[Tail Plane Icing]

t ¸ , _ _' Background The Aviation Safety Program initiated by NASA in 1997, in response to a call by the "Gore Commission" on improved aviation safety and security, has put greater emphasis in safety related research activities. Ice-contaminated-tailplane stall (ICTS) has been identified by the NASA Lewis Icing Technology Branch as an important activity for aircraft safety related research.

The ICTS phenomenon is characterized as a sudden, often uncontrollable aircraft nose- down pitching moment, which occurs due to increased angle-of-attack of the horizontal tailplane resulting in tailplane stall. Typically, this phenomenon occurs when lowering the flaps during final approach while operating in or recently departing from icing conditions. Ice formation on the tailplane leading edge can reduce tailplane angle-of-attack range and cause flow separation resulting in a significant reduction or complete loss of aircraft pitch control. At least 139 fatalities have resulted from 16 accidents involving primarily turbopropeller powered transport and commuter category airplanes caused by ICTS.

In 1991, the FAA initiated a comprehensive review of all aspects of tail plane icing and subsequent tailplane stalling of _u-bopropeller powered commuter and transport category airplanes. Results from this review process, as well as input from two recent international workshops on ICTS, prompted FAA to request NASA assistance in conducting research into the characteristics of ICTS.

In 1993, FAA and NASA embarked upon a four-year research program to address the problem of tailplane stall and to quantify the effect of tailplane ice accretion on aircraft performance and handling characteristics. The goals of this program, which was completed in March 1998, were to collect aerodynamic data for an aircraft tail with and without ice contamination and to develop analytical methods for predicting the effects of tailplane ice contamination. Extensive dry air and icing tunnel tests with a Twin Otter tail and a series of flight tests with a DeHavilland DHC-6 Twin Otter aircraft were performed. These tests resulted in a database of the aerodynamic effects associated with tailplane ice contamination for the Twin Otter aircraft.

Although the FAA/NASA tailplane icing program generated some answers regarding ice- contaminated-tailplane stall (ICTS) phenomena, NASA researchers have found many open questions that warrant further investigation into ICTS. In addition, several aircraft manufactures have expressed interest in a second research program to expand the database to other tail configurations and to develop experimental and computational methodologies for evaluating the ICTS phenomenon.

In 1998, the icing branch at NASA Lewis initiated a second multi-phase research program for tailplane icing (TIP II) to develop test methodologies and tailplane performance and handling qualities evaluation tools. A grant was awarded to Wichita State University to conduct and coordinate the research activities with support from the Bombardier/Learjet Company in

Wichita, Kansas. The main objectives of this new NASA/Industry/Academia collaborative

research program were as follows: 1. Define and evaluate a sub-scale wind tunnel test methodology for determining tailplane performance degradation due to icing.

.

Develop an experimental database of tailplane aerodynamic performance with and without ice contamination for a range of tailplane configurations. This database will support verification and development of analysis tools.

To accomplish the above objectives extensive wind tunnel tests were planned with a modem business jet (Learjet 45) and a twin engine low speed general aviation aircraft. These aircraft which are representative of general aviation aircraft were selected based on input from NASA and industry. Availability of high quality sub-scale wind tunnel models for these airplanes was an important factor in their selection. Use of available wind tunnel models reduced the cost of the research program significantly. Experiments with a full-scale empennage, a 25% sub-scale empennage and with a 15% sub-scale complete model of the Lear 45 business jet were planned to develop the experimental methodology. Selected flight test data for the Lear 45 horizontal tail were made available by Bombardier/Learjet to validate the experimental results obtained from wind tunnel tests of the sub-scale and full-scale models.

Tail specific configuration studies were included in TIP II to investigate the effect of horizontal tail location and to expand the tailplane performance database. The twin engine general aviation aircraft was selected for this study. This aircraft model has three tail configurations including a mid-tail, a cruciform tail and a T-tail.

This proposal provides a summary of the research activities performed during the first Year (July 1, 1998 - November 30, 1998) of this new research program and outlines the work tasks for the second year (12/1/98 to 11/30/99) of the TIP II program.

Summary of Work for Year 1 (7/1/98 to 11/30/98) The work tasks originally planned for Year 1 were as follows: 1. Obtain full scale Lear 45 empennage model and prepare it for testing 2. Generate and manufacture simulated ice shapes for testing. Two ice shapes generated with the NASA Lewis LEWICE code and sand paper ice will be tested along with the clean (baseline) configuration 3. Conduct tests in a large scale NASA tunnel to obtain, force, moment, hinge moment, pressure and flow visualization data.

4. Perform Reynolds number studies with the baseline and "iced" tail configurations.

5. Reduce and analyze the wind tunnel results and compare with available flight test data.

6. Obtain business jet sub-scale empennage and complete airplane models.

7. Obtain general aviation twin engine model.

8. Prepare progress report for Year 1.

Thesetasks,however,weremodifiedto accommodate wind tunnelschedules at NASA Ames

and at Wichita State University. Large-scalewind tunnel tests for the full-scale Lear 45

empennage originally planned for the fall of 1998 were rescheduledfor the spring of 1999

becausetest time could not be securedin the NASA Ames 40-tl x 80-11 wind tunnel facility

requiredfor the tests. Instead,the 25% sub-scaleLear-45 empennage was selectedfor testing

during the first year of the TIP II program.The original work tasksgiven abovewere replaced with the newtasksdescribed below: .

Conduct a computational study using the XFOIL computer code to investigate high and low Reynolds number characteristics of the LJ-267 airfoil section. The LJ-267 airfoil is the section for the Lear-45 horizontal tail. This task has been completed.

.

Select ice shapes for the wind tunnel tests of the 25% sub-scale empennage. Ice shapes selected include a 22.5 minute and 9 minute LEWICE generated shapes, 40, 80, 120 and 180 grit sand paper ice, as well as spoiler type ice shapes. This task has been completed.

. Conduct Navier-Stokes analyses with the clean and ice contaminated horizontal tail section for various Reynolds numbers and angles of attack to better understand the flow field characteristics. The 22.5 minute ice shape was used in these studies. This task has been completed.

.

Design and construct a new half-span horizontal tail for the 25% sub-scale Lear-45 empennage with pressure taps to obtain surface pressure distributions during the WSU wind tunnel tests. Pressure taps were incorporated at three spanwise locations. The construction of the tail was performed by Prototype Technologies, Inc in California. This task has been completed.

.

Design and construct 22.5 and a 9-minute LEWICE ice shapes for the 25% LEAR-45 horizontal tail model. Incorporate pressure taps into the 22.5-minute ice shape at the 50% and 90% spanwise locations. This task has been completed.

. Develop a test matrix for the wind tunnel tests at Wichita State University (WSU). This task has been completed. Details of this test matrix are provided in Table 1. The test matrix was reviewed by Learjet and NASA personnel.

Conduct extensive wind tunnel tests at the WSU 7-11 x 10-It wind tunnel facility with the ° 25% sub-scale empennage. These wind tunnel tests will start on September 24, 1998 and will end on October 16, 1998.

8. Analyze and process the experimental force, moment, hinge moment and pressure coefficients as well as the flow visualization data obtained during the WSU wind tunnel tests.

9. Develop a test matrix for the NASA Ames wind tunnel tests planned for the spring of 1999.

This task has been completed. Details of the proposed test matrix are provided in Table 2.

10.Participatein a pre-testmeetingat the NASA Ames 40ft x 80ft wind tunnel facility to plan the full-scale Lear-45 empennage tests. This meeting will take place on October 19 and 20 of 1998.

11. Initiate progress report for the work performed during the first Year of TIP II.

Work Tasks for Year 2 (12/1/98 to 11/30/99) The proposed tasks will provide full-scale data for the business jet aircraft to verify the sub-scale methodology. Proposed work tasks for year 2 of TIP-II are as follows.

1. Complete progress report of work performed during Year 1 2. Obtain full scale business jet empennage model and prepare it for testing 3. Generate and manufacture simulated ice shapes for testing of the full scale Lear 45 empennage. A 22.5 min ice shape with and without roughness, a 9 rain ice shape as well as 40 and 120 grit sand paper ice will be tested along with the clean (baseline) configuration.

The 22.5 and 9 minute shapes were generated with the NASA Lewis LEWICE ice accretion code.

4. Conduct tests in the 40-ft x 80-fl NASA Ames wind tunnel to obtain, force, moment, hinge moment, pressure and flow visualization data. Test details are given below.

5. Perform Reynolds number studies with the baseline and "iced" tail configurations.

6. Reduce and analyze the wind tunnel results and correlate with available flight test data as well as with the sub-scale test results obtained during Year 1.

7. Prepare final report for the work conducted during Year 1 and Year 2.

8. Obtain the Lear 45 15% sub-scale complete airplane model and prepare it for testing. This airplane will be tested in year 3 of TIP II.

9. Obtain twin engine general aircraft model and prepare it for testing. This is a 1/5 scale model with three different tail configurations: mid-tail, cruciform tail and T-tail. This model will be tested during year 3 of the TIP II program.

10. Develop a test matrix for the complete Lear 45 and twin engine general aviation models Isee items 8 and 9 above).

Wind Tunnel Tests of Lear-45 full-scale empennage at NASA Ames 40'x80' Tunnel Facility Test variables for the wind tunnel tests of the full-scale empennage include angle of attack ((x), sideslip (13), elevator deflection (5), ice shape, and Reynolds number (Re) as shown in Table 2. Angle of attack sweeps l_om 0 to -25 degrees will be performed in increments of 1 degree to resolve the behavior of the force and moment coefficients (26 alphas). Sideslip angles of 0 to 16 ° in increments of 1 degree will be considered. Elevator settings of -15 °, -10 °, 0 °, +10°and +15 ° will be tested. Two artificial ice shapes will be tested as well as sand paper ice.

The proposed ice shapes will be obtained using the NASA Lewis LEWICE code and will include a 22.5 minute glaze ice and a 9 minute ice shape. In addition, 40 and 120 grit sandpaper will be used to simulate roughness effects. Two airspeeds will be used in most of the tests to provide two

Reynoldsnumbers.Oneof the Reynoldsnumberswill be selected to matchflight test conditions

for comparingthe full scalewind tunneldatawith flight test data.The secondReynoldsnumber

will be set to match the 25% Lear-45 sub-scalewind tunnel tests.Limited Reynoldsnumber

studieswill alsobe conductedfor selectedtest configurations.Test measurements will include

force,moment, andhingemomentdata.For selectedcases, pressure andflow visualizationdata

will also be obtained. Surfacepressuremeasurements will be conductedwith pressurebelts.

Flow visualizationwill beperformedwith tufts.

Proposed Costs

The proposed budget for Year 2 is given in Table 3. A time period of one year is requested to complete the tasks described above starting December 1, 1998.

A subcontract will be awarded to the Bombardier/Learjet Company in Wichita to support the wind tunnel tests during Year 2. In addition, Learjet will provide flight test data for comparison with the wind tunnel experiments.

NASA Lewis will cover the cost of the full-scale Lear-45 empennage wind tunnel tests at the NASA Ames 40-ft x 80-ft facility. Note that this cost is not included in the attached budget (Table 3).

Personnel Dr. Michael Papadakis (PI) and Mr. David Ellis (Co-PI) will lead the proposed research effort and they will be assisted by one graduate student and one undergraduate student. In addition, a subcontract will be awarded to the Learjet Company in Wichita to assist with the wind tunnel tests.

Dr. Papadakis has had over 18 years experience in experimental and computational aerodynamics. His experimental research includes water droplet impingement on aircraft surfaces, single and multi-element airfoil flow field experiments, gnmey flap studies, tunnel wall correction methods, jet flows for STOVL aircraft applications and turbulence measurements on a McDonnell Douglas airfoil with vortex generators. He has also performed extensive research in computational aerodynamics. He has developed two-dimensional panel and Navier-Stokes computer codes and has conducted computational investigations on massively separated flows about single and multi-element airfoils. During his work at PILATUS aircraf_ in Switzerland, he participated in various flight test activities of the PC-7 aircraft.

Mr. David Ellis is Director of Research and development at NIAR. He received a B.S.

degree in Aeronautical Engineering from the University of Colorado and an M.S.E. (aero) degree from Princeton University. He has had 35 years of experience in flight research, teaching and airplane design and development. He was directly involved in the icing certification and testing of the Cessna T303 Crusader aircraft. He also carried out the T303 tailplane icing investigation program.

Michael Papadakis (PI) - (Short Biographical Sketch) Current Position: Associate Professor, Department of Aerospace Engineering, Wichita State University, Wichita, Kansas, 67260-0044, Tel: (316) 978-5936, Fax: (316) 978-3307, E-Mail: papadaki@twsuvm.uc.twsu.edu Academic Degrees: Ph.D. Aeronautical Engineering, Wichita State University, Wichita, KS, 1986 M.S. Aeronautical Engineering, Loughborough University, England, UK, 1981 B.S. Aeronautical Engineering, Loughborough University, England, UK, 1979 Recent Honors and Awards: • Bombardier/Learjet Fellow, 1998-2001 • Wichita Section AIAA Best Technical Paper Award, June 1997 • Boeing Fellow, September 1992-1995 • University of Wichita Regent's Award for Excellence in Teaching, Wichita State University, May • DOW Outstanding Young Faculty Award, ASEE Midwest Section, March 1991 Professional Affiliations: Member of the American Institute of Aeronautics and Astronautics Member of the American Society of Engineering Education Publications Over 55 articles have been published in refereed journals and conference proceedings. In addition, a book and a number of contractor reports have been authored. Selected publications related to icing research are provided below.

Selected Refereed Publications 1. M. Papadakis, M. Seltmann and S. Experimental Study of Simulated Ice Shapes on a NACA 0011 Airfoil," AIAA Paper 99-0096, AIAA 37th Aerospace Sciences Meeting and Exhibit, Reno, NV, January 11-14, 1999.

2. M. Papadakis, G.T. Vu, E.K. Hung, C.S. Bidwell, T. Bencic and M.D. Breer "Progress in Measuring Water Impingement Characteristics on Aircraft Surfaces" AIAA Paper 98-0488, AIAA 36th Aerospace Sciences Meeting and Exhibit, Reno, NV, January 12-15, 1998.

3. M. Papadakis, R. Elangovan, G.A. Freund, and M.D. Breer, "Methods for Obtaining and Reducing Experimental Droplet Impingement Data on Arbitrary Bodies," AIAA Journal of Aircraft, vol. 28, Number 5, May 1991.

4. M. Papadakis, R. Elangovan, G.A. Freund, and M.D. Breer, "Water Droplet Impingement on Airfoils and Aircraft Engine Inlets for Icing Analysis," AJAA Journal of Aircraft, vol. 28, Number 3, March 1991.

5. M. Papadakis, M.D. Breer, N.C. Craig, and C.S. Bidwell, "Experimental Water Droplet Impingement Data on Modem Aircraft Surfaces," AIAA-91-0445, AIAA 29th Aerospace Science Meeting, Reno, Nevada, January 7-10, 1991.

6. G.A. Freund, F.M. Dickey, R. Elangovan, M.D. Breer, and M. Papadakis, "An Automated Optical Instrument for Extracting Water Droplet Impingement Data from Wind Tunnel Experiments," SPIE 81824, SPIE's 31st Annual International Technical Symposium on Optical and Optoelectronic Applied Science and Engineering, August 16-21, 1987.

7. M. Papadakis, G.A. Freund, R. Elangovan, and M.D. Breer, "Experimental Water Droplet Impingement Data on Two Dimensional Airfoils, Axisymmetric Inlet and Boeing 737-300 Inlet," AIAA- 87-0097, Invited Paper, AIAA 25th Aerospace Science Meeting, Reno, Nevada, January 12-15, 1987.

8. M. Papadakis, G.W. Zumwalt, J.J. Kim, R. Elangovan, G.A. Freund, W. Seibel, and M.D., Breer, "An Experimental Method for Measuring Droplet Impingement Efficiency on Two and Three Dimensional Bodies," AIAA-86-0406, AIAA 24th Aerospace Science Meeting, Reno, Nevada, January 6-9, 1986.

David R. Ellis

14505Willowbend Circle

Wichita, KS 67230

(316)733-0165

EDUCATION University of Colorado B.S. Aero. Eng. 1957 M.S.E. Aero 1962 Princeton University EMPLOYMENT Mr. Ellis is presently Director, Research and Development, at the National Institute for Aviation Research, Wichita State University, where he oversees wind and water _nnels, and structures, materials, impact dynamics, flight simulation, propulsion, icing, and cryogenics laboratories.

Industry positions have included that of V.P. of Engineering at Commander Aircraft and Manager of Advanced Design and Systems Research at Cessna Aircraft; in the latter post he was in charge of design and development of the Model T303 Crusader and the Model 208 Caravan, and directed major research programs in laminar flow wing technology, electro-impulse de-icing systems, and advanced general aviation engines.

He has been an Associate Professor of Aerospace Engineering at the University of Kansas and an Adjunct Associate Professor of Aerospace Engineering at Wichita State University. As Manager of Flight Dynamics Research at Princeton University, he led the development and use of variable stability in-flight simulators for flying qualities research.

He worked as an aerodynamicist in two different full-scale wind tunnels at NACA and NASA, and has consulted extensively in the areas of airplane design, flying qualities, and ice protection.

OTHER ACTIVITIES Mr. Ellis served on NASA's Aeronautical Research and Technology Subcommittee and on NASA Ad Hoc Committees on general aviation, flight research, and advanced materials. He has served in the past on Congressional, National Academy of Science, and Department of Energy advisory committees.

He has served on the General Aviation Manufacturers Association Technical Policy Committee, and currently represents GAMA on international committees dealing with harmonization of U.S. and European airworthiness regulations and with aging commuter aircraft.

Mr. Ellis is an Associate Fellow of AIAA and past chairman of the AIAA General Aviation Systems Technical Committee. He is a participant in SAE aeronautical activities.

He is a former flight instructor and research pilot.

Table 1 - Test Matrix for 25% sub-scale Lear-45 empennage tests at WSU Test Facility: WSU 7-ft x 10-ft Wind Tunnel Test Dates: September 24 to October 17, 1998 Experimental Data: Force, moment, hinge moment and pressure coefficients Number of Test Runs: 242 Simulated Ice Shapes for Horizontal Tail • L22: Lewice 22.5 minute ice shape with smooth surface scaled to model size (scale = 1/4) • L22B: Lewice 22.5 minute ice shape with beads; scaled to model size (scale = I/4). Simulate beads with 24 grit • LgB: Lewice 9 minute ice shape with beads; scaled to model size (scale = 1/4). Simulate beads with 24 grit • $40:40 grit sandpaper. Cover surface as shown in Fig. 1 • $40-10:40 grit sandpaper. Cover surface from 10% chord on lower surface to 10% chord on upper surface • $80:80 grit sandpaper. Cover surface as shown in Fig. 1 • S120:120 grit sandpaper. Cover surface as shown in Fig. 1 • S180:180 grit sandpaper. Cover surface as shown in Fig. 1 • S180-10:180 grit sandpaper. Cover surface from 10% chord on lower surface to 10% chord on upper surface • SP47C: Spoiler - 4.7mm Constant height. Place at 2% chord on tail lower surface (4.Tmm, 4.7/312.7375=0.015MAC) • SP47V: Spoiler - 4.7mm Variable height (h) but constant (h/local c). Place at 2% chord on tail lower surface (4.7mm, 4.7/312.7375--0.015MAC) • SP94C: Spoiler - 9.4mm Constant height. Place at 2% chord on tail lower surface (9.4mm, 9.4/312.7375=.03 MAC) • SP94V: Spoiler - 9.4ram Variable height (h) but constant (h/local c). Place at 2% chord on tail lower surface (9.4mm, 9.4/312.7375=.03 MAC) Tail Root Chord = 16.35 in, Tail Tip Chord = 7.04 in, Tail Span=51.56 in, MAC = 12.31 in (312.74mm), Tail Area = 603.135 sq in, 4.189sq ft Horizontal Tail Setting = -9 degrees Alpha Sweep (body): +9 ro -16 in 1 deg. increments (26 alphas) (note: alpha range for tail = 0 to -25) Beta Sweep: -16 to 16 in 2 deg. increments (17 betas) 50 psf, 121.4 kts, 139.8 mph, 205f/s, 62.5 m/s, Re=l,300,000/ft Tunnel Q = 15 psf, 66.5 kts, 76.6 mph, 112.3f/s, 34.2 m/s, Re=710,000/ft Tunnel Q = 5 psf, 38.4 kts, 44.2 mph, 64.84f/s, 19.8 m/s, Re=410,000/ft Tunnel Q = Transition strips for horizontal and vertical tail: Boundary Layer transition dots (Boeing Cylinders).

Location of transition strips : At 10% chord upper and lower surface. Size: 0.007 inches Boundary Layer Profile Measurements will be conducted for selected test configurations with a boundary layer mouse located at 65% MAC. The velocity profiles will be used to compare boundary layer behavior due to the ice shapes and sandpapers.

Test Elevator Surface Sweep Q Ice Shape Data # Deflection Points psf NA 0 50 none (clean) alpha, beta=-16,0,16 NA 0 alpha, beta=-16,0,16 104 15 none (clean) NA 0 104 5 none (clean) alpha, beta=-16,0,16 NA 0 Beta, alpha=+9,-6,-16 51 50 none (clean) NA 0 51 15 none (clean) Beta, alpha=+9,-6,-16 NA 15 104 alpha, beta=-16,0,16 50 none (clean) NA 15 15 none (clean) alpha, beta=-16,0,16 NA 15 104 alpha, beta=-16,0,16 5 none (clean) NA 78 9 alpha 50 none (clean) NA 78 alpha 10 15 none (clean) NA 0 104 11 50 L22B alpha, beta=-16,0,16 NA 0 104 12 15 L22B alpha, beta=-16,0,16 NA 0 104 13 5 L22B alpha, beta=-16,0,16 0 51 NA 14 50 L22B Beta, alpha=+9,-6,-16 NA 0 51 15 15 L22B Beta, alpha=+9,-6,-16 NA 15 16 5O L22B alpha, beta=-16,0,16 NA 15 104 17 15 L22B alpha, beta=-16,0,16 NA 15 alpha, beta=-16,0,16 18 5 L22B NA alpha 19 5O L22B NA 20 15 L22B alpha NA 21 50 L22 alpha, beta=-16,0,16 NA alpha, beta=-16,0,16 22 15 L22 NA 23 5 L22 alpha NA 15 104 alpha, beta=-16,0,16 24 50 L22 NA 15 25 15 L22 alpha, beta=-16,0,16 NA 15 alpha 26 5 L22 NA alpha 27 50 L22 NA alpha 28 15 L22 NA 0 alpha, beta=-16,0,16 29 50 $40 NA 0 alpha, beta=-16,0,16 30 15 $40 NA 0 alpha 31 5 $40 0 51 NA 32 50 $40 Beta, alpha=+9,-6,-16 NA 0 Beta, alpha=+9,-6,-16 33 15 $40 NA 15 alpha, beta=-16,0,16 34 50 $40 15 104 NA alpha, beta=-16,0,16 35 15 $40 NA 15 alpha 36 5 $40

NA 78

37 50 $40 alpha

38 15 $40 NA 78

alpha

NA 0 104

39 50 $120

alpha, beta=-16,0,16

0 104

40 15 $120 NA

alpha,beta=-16,0,16

NA 0 26

41 5 $120 alpha

NA 0

42 50 $120 Beta,alpha=+9,-6,-16

NA 0 51

43 15 $120 Beta,alpha=+9,-6,-16

NA 15 104

44 50 $120 alpha, beta=-16,0,16

NA 15

45 15 $120 alpha, beta=-16,0,16

NA 15 26

46 5 $120 alpha

NA 78

alpha

47 50 $120

NA alpha

48 15 $120

0 104

NA alpha, beta=-16,0,16

49 50 L9B

NA 0 104

alpha,beta=-16,0,16

50 15 L9B

NA 0

51 5 L9B alpha

NA 0 51

Beta,alpha=+9,-6,-16

52 50 L9B

0 51

NA

53 15 L9B Beta, alpha=+9,-6,-16

15 104

NA alpha, beta=-16,0,16

54 50 L9B

NA 15

55 15 L9B alpha, beta=-16,0,16

NA 15

alpha

56 5 L9B

NA

alpha

57 50 L9B

NA alpha

58 15 L9B

NA

alpha,beta=- 16,0,16

59 50 $80

NA

alpha,beta=-16,0,16

60 15 $80

NA 15

alpha, beta=-16,0,16

61 50 $80

NA alpha, beta=-16,0,16

62 15 $80

NA

alpha, beta=-16,0,16

63 50 $180

NA

alpha, beta=-16,0,16

64 15 $180

NA alpha, beta=-16,0,16

65 5 $180

NA 0

5O $40-10 alpha, beta=-16,0,16

NA 0

15 $40-10 alpha, beta=-16,0,16

NA alpha, beta=-16,0,16

5 $40-10

NA 0

50 $180-10 alpha, beta=-16,0,16

NA 0

15 $180-10 alpha, beta=-16,0,16

NA alpha, beta=-16,0,16

71 5 $180-10

alpha, beta=-16,0,16

72 50 SP47C Lifting (lower)

alpha, beta=-16,0,16

15 SP47C Lifting (lower)

alpha, beta=0

74 50 SP47C Lifting (lower)

75 15 SP47C Lifting (lower) 15 alpha, beta=0 26

76 50 SP47V Lifting (lower) 0 alpha, beta=-16,0,16

77 15 SP47V Lifting (lower) 0 alpha, beta=-16,0,16

alpha, beta=0

78 50 SP47V Lifting (lower) 15

79 15 SP47V Lifting (lower) 15 alpha,beta=0

80 50 SP94C Lifting (lower) 0 alpha, beta=-16,0,16

81 15 SP94C Lifting (lower) 0 alpha, beta=-16,0,16

alpha, beta=O

82 50 SP94C Lifting (lower) 15

83 15 SP94C Lifting (lower) 15 alpha, beta=O

84 50 SP94V Lifting (lower) 0 alpha, beta=-16,0,16

85 15 SP94V Lifting (lower) 0 alpha, beta=-16,0,16

alpha,beta=0

86 50 SP94V Lifting (lower) 15

87 15 SP94V Lifting(lower) 15 alpha,beta=0

FLOW VISUALIZATION (Microtufts)

alpha, beta=0,-16

88 50 none(clean) NA 0

alpha, beta=0,-16

89 15 none(clean) NA 0

alpha, beta=0,-16

90 50 none(clean) NA 15

alpha,beta=0,-16

91 15 none (clean) NA 15

alpha, beta=0,-16

92 5O L22B NA 0

alpha, beta=0,-16

93 15 L22B NA 0

94 50 L22B NA 15 alpha, beta=0,-16

alpha, beta=0,-16

95 15 L22B NA 15

96 50 L22 NA 0 alpha, beta=0,-16

97 15 L22 NA 0 alpha, beta=0,-16

alpha, beta=0,-16

98 5 L22 NA 0

alpha, beta=0,-16

99 5O $40 NA 0

alpha, beta=0,-16

100 15 $40 NA 0

101 50 $40 NA 15 alpha, beta=0,-16

alpha, beta=0,-16

102 15 $40 NA 15

103 50 $180 NA 0 alpha, beta=0,-16

104 15 $180 NA 0 alpha, beta=0,-16

alpha, beta=0,-16

105 50 $180 NA 15

106 15 $180 NA 15 alpha, beta=0,-16

alpha,beta=0,-16

107 50 SP47C Lifting (lower) 0

alpha, beta=0,-16

108 50 SP47V Lifting (lower) 0

alpha, beta=0,-16

109 50 SP94C Lifting (lower) 0

110 50 SP94V Lifting (lower) 0 alpha, beta=0,-16

Boundary Layer Profile Measurements at 65% MAC ( Select Cases from tests 1-87) REMOVE HORIZONTAL TAIL 111 50 none (clean) NA 0 alpha, beta=-16,0,16 alpha, beta=-16,0,16 112 15 none (clean) NA 0 113 50 none (clean) NA 0 Beta, alpha=+9,-6,-16 Beta, alpha=+9,-6,-16 114 15 none (clean) NA 0 0.50 [ 0.40 : i i 0.30 !50 in 0.20 0.10 e g} q t- O 0.00 t-- _il section °m _7 Airfoil >., -0.10 on Surface I -0.20 -0.30 -0.40 -0.50 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1.0 x (inches) Figure 1 : Sand paper coverage for upper and lower surfaces of Lear-45 horizontal tail Table 2 - Test Matrix for full-scale Lear-45 Empennage Tests at NASA Ames 40-ft x 80-ft Tunnel Note: ahtsweep=[O,-2,-4,-6,- 7,-8,-9,-l O,-l l,-12,-I 3,-I 4,-15,-16,-17,-18,-19,-20,-21,-22,-23,-24,-2 5] - 23 alphas b sweep=[O to 16 deg in 1 deg increments] - 17 angles of sideslip MAC =1.25 meters Set horizontal tail incidence to -9 deg with respect to fuselage axis Vel alpha beta RU Test Type Ice Shape dE Re No. Ma N (knots) (deg) (deg) # 116 a sweep 0 1 Flow Angularity clean 0 5,102,227 0.18 116 0 b sweep 2 Flow Angularity clean 0 5,102,227 0.18 31_ a sweep ff _l Alpha Sweep clean 0 1,337,135 lEO5 30.4 a sweep 0 9 Alpha Sweep clean -10 1,337,135 0.05 30.4 a sweep 0 10 Alpha Sweep clean -15 1,337,135 0.05 30.4 a sweep 0 11 Alpha Sweep clean 10 1,337,135 0.05 30.4 a sweep 0 12 Al_p_ clean 15 1,337,135 0.05 a sweep -I! i'g Alpha Sweep 22.5 min w/beads 0 1,337,135 IEOS- 30.4 a sweep 0 19 Alpha Sweep 22.5 min w/beads -10 1,337,135 0.05 30.4 a sweep 0 20 Alpha Sweep 22.5 min w/beads -15 1,337,135 0.05 30.4 a sweep 0 21 Alpha Sweep 22.5 min w/beads 10 1,337,135 0.05 30.4 a sweep 0 22 Alpha Sweep 22.5 min w/beads 15 1,337,135 0.05 a sweep -0 2_ Alpha Sweep 40 grit sandpaper 0 1,337,I35 1EOS 30.4 a sweep 0 29 Alpha Sweep 40 grit sandpaper -10 1,337,135 0.05 30.4 a sweep 0 30 Alpha Sweep 40 grit sandpaper -15 1,337,135 0.05 30.4 a sweep 0 31 Al[Iha Sweep 40 grit sandpaper 10 1,337,135 0.05 30.4 a sweep 0 32 Alpha Sweep_ 40 grit sandpaper 15 1,337,135 0.05 a sweep ff YS" Alpha Sweep 120 grit sandpaper 1) 1-733"7,T3-5 -07iY5 30.4 a sweep 0 39 Alpha Sweep 120 grit sandpaper -10 1,337,135 0.05 a sweep 120 grit sandpaper -15 1,337,135 0.05 30.4 Alpha Sweep a sweep 120 grit sandpaper 10 1,337,135 0.05 30.4 Alpha Sweep a sweep 12!) g_a_er 15 1,337,135 0.05 30.4 Alpha Sweep a sweep Alpha Sweep a sweep Alpha Sweep 0 52 a sweep Alpha Sweep a sweep Alpha Sweep 10% local c coverage 10% local c coverage 0 59 10% local c coverage a sweep 120 grit sandpaper 0 1,337,135 0.05 30.4 Alpha Sweep 0 60 10% local c coverage a sweep 120 grit sandpaper 15 1,337,135 0.05 30.4 Alpha Sweep 10% local c coverage 10% local c coverage 10% local c coverage a sweep Alpha Sweep 10% local c coverage a sweep r_ Alpha Sweep a sweep Alpha Sweep a sweep Alpha Sweep 0 77 a sweep 40 grit sandpaper 0 2,199,236 0.08 50 Alpha Sweep 0 78 a sweep 40 grit sandpaper 0 3,078,930 0.11 70 Alpha Sweep 0 79 a sweep 40 grit sandpaper 0 4,046,594 0.14 92 Alpha Sweep 0 80 a sweep 40 grit sandpaper 0 6,157,860 0.21 140 Alpha Sweep 0 81 a sweep 40 grit sandpaper 0 7,037,554 0.24 160 Alpha Sweep 0 82 a sweep 40 grit sandpaper 0 7,917,249 0.27 180 Alpha Sweep Alpha Sweep 22.5 min from IRT 0 2,199,236 0.08 50 a sweep 0 89 Alpha Sweep 22.5 min from IRT 0 3,078,930 0.11 70 a sweep 0 90 Alpha Sweep 22.5 min from IRT 0 4,046,594 0.14 92 a sweep 0 91 Alpha Sweep 22.5 min from IRT 0 6,157,860 0.21 140 a sweep 0 92 Alpha Sweep 22.5 min from IRT 0 7,037,554 0.24 160 a sweep 0 93 Alpha Sweep 22.5 min from IRT 0 7,917,249 0.27 180 a sweep 0 94 Alpha Sweep 120 grit sandpaper 0 2,199,236 0.08 50 a sweep 0 101 Alpha Sweep 120 grit sandpaper 0 3,078,930 0.11 70 a sweep 0 102 Alpha Sweep 120 grit sandpaper 0 4,046,594 0.14 92 a sweep 0 103 Alpha Sweep 120 grit sandpaper 0 6,157,860 0.21 140 a sweep 0 104 Alpha Sweep 120 grit sandpaper 0 7,037,554 0.24 160 a sweep 0 105 Alpha Sweep 120 grit sandpaper 0 7,917,249 0.27 180 a sweep 0 106 Beta Sweep 22.5 min w/beads 0 _ -071-8 Ti'b- "0 _p I-0"9 Beta Sweep_ 22.5 min w/beads 0 1,337,135 0.05 30.4 0 b sweep 110 Beta Sweep 120 grit sandpaper 0 _,_5 0.-0S_ 3"0-.-.K V 35"sweep "IT3 Beta Sweep 120 grit sandpaper 0 1,337,135 0.05 30.4 0 b sweep 114 Flow Visualization clean 0 5,102,227 0.18 116 a sweep 0 115 Flow Visualization clean 0 5,102,227 0.18 116 0 b sweep 116 Flow Visualization 40 grit sandpaper l_ -5,Ili27227 l)TFff _ a sweep "ff Yi'9 Flow Visualization 40 grit sandpaper 0 5,102,227 0.18 116 0 b sweep 120 Test measurements: Force, Momemt, Hinge Moment and Pressure Coefficients. In addition, boundary layer measurements will be conducet for selected test cases with a boundary layer mouse located at 65% MAC.

Certificati0as Appeadix E CEFrr]FICATIONS REGAJqOIHG LOBBYING; 0EBARMENT. SUSPENSION AND OTHER RESPONS[BILrrr MATTERS; ANO DRUG-FREE WOR KPLACE REQUIREMEN-rs AppllcazrL_ _l-_ould reler {o Ihe regul_Jor_ c_Bd below Io dele.-T_n.e the c:Bn_$c_lz$orl to wt_ic.h U'_y ar_ Peq=Jired to a._le.Et. A_pl_a.c_,: _uld aL_o r_v_ew lhe In_ruOtor_ Io¢ cedMI___Iion Included In the regulaIIor_ belore oorn_tlng I_L_ form. S1gna.lure ol II_s form provldes lot compi1_n<:e wtlh o_rIMIcaIIon re_ulremeRIs under 34 CFR Parl 82.. "New Ae_rIc:Ior_ on LobOylng," and 34 CFR Pad _3. "Govemmenl-WIOe O_io_rrnent acK:l Su:s_o,'_Jon (Nonprocur_mer_) and GovemmontIWlde Requlmrr_nts lot Oruq-Fm, e Workplace (Or&n_)." TP, o c.aa_k:atk)ns sl_a_l O_ trsated a.s a maJerial repl'et,.entellon of tad upon whk::n rellat'_c:e MII be placed w'h_n the 0.ep&,'tmenl of Educmtk_n determlr'_s to aw&rd tt_ Oovered _ra_ac_n, _ar_ or co,op_ralNe agreem-ent.

4. LO88"rlNG vh3la.t_on ot a crlmln.al drug s_alu(e oc..curdrKj' tn _ wo, r_ce r_ laler _ live C:a_r'_az days allot suGh C_r_tc_lon: A__ required by Section 1352. Trl_ 31 ol the U.S. Code. and (e) Nolrtylng the agency. In ",,,'r':tng. ',,_i'_n 10 ca_,n,d.a/ day'_ attar r_r_..elvlng i'_,o_ ur',dar s_bp_'_gra.ph (d)(2) Irom an empk:_e.e or I_ed al 34 CFR Part &?.. lOT pe_-cs er_e,_ into a Qr_r_ o_ _tNe egreerr_enl over $100,000, a.s de_r_d at 34 CFR part o_r_ rer__Vg ac_u.aJ n.o6ce of _ conv_cdor_ Err_oyers E2, S.ec_; 82.105, and 8:7._110. Ihe applk_r_ c_rtl1_es _"_I: ol oorrv_.L-'ted err_lo,/ee_; mu= pmv_e notice, including posrl_on ml.e. to: OW-_clor. Gr_u_Ls _ Corru-a<:=.s Servl_a, U.S. D_paztn'_nI (a) No Federel _pproii:_la.led fund3 have D-e_n paJd or Will be !::_dd, o; Educ.zUIon, 400 MarTI_Lnd Avenue. S.W.(Ro.om 312A, GSA I:_ _' on behe_ ol the under.ned. Io _ _ to_ Lnri_rK2 _r Ae.g_onaJ o,rt_<:_, Bullclb",g No. 3). W_shlr:,_on, OC 20_024571.

II_er1_li"_ to I;llhJ_rK_l_ _ ollk:IN" or efr_p_::)yee Of _ a-gein'cy, a Nottc.e _ V',OJde the _ntillr._k_n numbers(s) of ead_ atfec:ed Me_ber ol Cot',gins.% an ortk:_r or en_k:_ee ol Cor_m.s_. or an efnploy_ cW a Me_ ot C.orx_r'e:_ [n _nn_<:tW_n _h me maJ_ng I; l)_eX_ng one ot the to_lowtr_g ectlor_, wlth_ 30 c_.er, d_a.r _ o_ of any Fed.er_ gr_nl, th_ enterlr_g Ir_o ol _ c.,ooperall_e l'_a.cel_lng noboa u.r_,er s.ubp&r_gr_ph (C0(2). wtlh res_-e_ to _0' agre.e,n_l, and tt_ exlertsk)n, conllnu_ll<_, rer).ew&l. _rr, e,r_Irn, e_.

en_k_ye.e who Is .T..o o:x'rvld_K_- or mod]t_bn ol _ Fe<_e_-al gran_ o_ cooOera-b_ve ,_gr_eme_t: (b) I'I _ny tu-n<_ o_I_e¢ than FederaJ s_orop_l_d lur,_ I_ve been (I) TaJdr_g ,_(::_pf_:x_te p.(w3.on.,-w}l a(:::tJ<_ aga.Lr_1 _ _ employee.

Jdo_ _ be paJd to an' 7 per_n loT _rliuar, dng or si'terr(X_g to up to _ #_dudln_ termlo._l_on, oon:s_lert with the requlmrr_nt_ o_ tt_.e Re_'_bli",_:t_n Act o_ 1973, a__ ab'ner_e_; or nc_ an oh'k_r or err, pk)yee or _ =_r'_c'y. a Member ot _. an ol't1<:_ or empl,oy_e ot Cor, gr_, _ an em,ploye-e o_ CZ} Requ_r'r_ :_uon _,'r_k:_ee to pi.r'J_p_le _.II_ac_orIi7 _ a drag Me_r ol Congr=)s3 In corv_c_n w_h ihl:s Fe_raJ or"_rt or _hu._a a.._r,_L,_P,o_ or ret'_,bi_l_,flon program .'kooroved lot _,,.uch CooperalNe agr'e-err_r_, the u_r_Jgned 31"_II complele and pu_:x_es by a Federa L S_a_e. or k_-.._l h.e._Rn, law entorc:_m-er_ o< _uOrn_ _a.rx_rd Form - ILL. -Ol:sOo_.ure Form _o Report _ing." _her s_pa_e agenc,/.

_n a_oorda;_e wtU_ _b k-i_ru_k_s: (g) Ma.X_ng a good ta._lh egod to o0_tnue to malnl_ln a d.rug-tre-o (c) The un, d.er_ned _ll requ_'e that the LaP,guage ot thks worW:pCace mmugtl Irnpi._n-enlaL_n ot pa.ragrap_ (a), Co). (c). (d).

c_rl_IIon be L.'_dud.ed In i't_e a_,,,-'aJ'd d_,<:un"_r_s lot _ll _ubawerd _e)._r0.

al a" t)er_ (ln<:ludlng _ubgr_nt_. cor_ra_'J under grills and • _ g,'3J'tlee may Ir_rt in _ _ce prov_ed below the _tles(s) r..OoperelNe agreemenl_, end _ul::Eomra_s) and that ell tot t_a I>edo_ ol worX dope tn conr_c_0n _ the _pectfk: :mbr_,clp_r'_..._h.al.l Certlly _ di:r,.do:_ eooo.,'dlr, g_/.

oI Pertorm_n<:e (Slreel admires3, crty. county, slale. _p 2. EF._BARMENT, SUSPENSION, ANO OTHER RESP<3NS_BILFPr co<_) M.ATFERs r_qulred by Execultve Order 12S49. Debermen( and 1845 Fairmount Su_r_,on. _ _mpl_rr_nled at 34 CFR Part aS. tot pro:sOectNe p_u't_IE:_u'w._ _ pdrr_nu'y c=:)ve_redl,'-_-',,__:tk}r_, _s deft,ned a/ 3.4 CF_ Part 8.5,Se<::tiof_ 8.S.IQS and 85.100 - Wichita, KS 67260 Sedgwick County A. The appBc:a4'w c:_rt_ha_:b"_.l it and _._ prW',,cJpa.ks: { ) _I there _r_ _or_:_ac_ on 111_ lI_t _ not IdenlIII¢<I (a) Ate not pre=entty de0arred, sue.pen<tied, proposed tot he_.

debarrn._nt, deClared In.ellgible. or votunlartly excluded from covered l:r_'_Icllons by _ Fe.det_l Oepanrne_ or agency;.

ORUG-FFLEE V_CE ('b) Have not w_zI'_n a mree-year p_rlod pm<:e,dtng thls _Ik:_I_n (gr_'_ee:_ wt_ _ I_<_dua_) been cortvt<:_ed _ or I'_d a C_II J.udgm._l rendered _ _-,em As required by the Opug-Free Workplace Act of lgBe. aund lot' oOr_n o_ hlud or a c:_.'ntn.aJ otler_-_ tn conn-ec1_on v(Ith _lE_efr_r_d at 34 CFF_ Pad 83. SL.i3pan F. to_ _ra_ee_. a._ defined obtai,,'_Ig, atlem,ptln 0 to obtain, o_r l:>edorrnlng a pub_: (FederaJ.

a_ 34 CFR _ 8S. S.e<:_ 83.60'3 _md 85.610 -- Slate, or local) _lo,q _ oontr-a_ ur, d_ a pub4tc tF_s.,_tlo_: A. A_ a cond_on o_ _ _r_. I CediS/ tr_ I wlI n<X en_age In 0he '_3La.tk3n Of Fe_er"_ or Stats a._tr'_l_ =taJutes or commL_k:_l Ot e,'TW:_,zzJ_n'_r'_, b%en. torero/, bribery, fl_.ffk::_I_ o_" de:_r'LK:_on ot ol a o0nl,roll, e,d ._sta_Ca in co_c_Iog any ac_;'v_ty wllh the _r-A_: re(::_n3:s, m.lldng false _.l.alerr_nls. or r'_::eMr_ s_ot.e._ pl'Op.etl_.

_nd (C) Are not pre:_,nlI'y Ir_Icled lot or oI_ c_mlr_Jly or cI'vII_ B. It c_':.vI_ed ol a cHm,lnaJ drug oner_e re.sutIin.g t,,om a vloLa;Son by a govemn_r_al entry (Federal. Stale. or kx:_r/ wffh o<:cun'Ing d,adng lhe c_r',duc_ ot _ granl ac:Itvtty.I will mpon m,e commi:s_J,o_ ot lu',yot _ offen.sa_ enun',er_ed In pa_"agraph (1)(b) convl,c_1.on. In wrIIk-,g,w1_i'_n 10 c:_lend.ar day_J oI the conviction, to,'.

o4 _ Certntc_t_o_; and E4n_c_or G_ _ Contracts SerHce, U.S. Oepa_rlm.enI ol (d) Hive mo_ _hln a thee.e-year p_rk>d pre<::edW'_ lh_ _plk::_ktlon Educallon, 40(} MaryLand Avenue, S.W. (Room 3124. GSA I'_Id one or mot_" publk:; _rar_:ac_)or_ (FeOe_.l. Slale, or k>caJ} Regional Oft_e BulldOg No. 3). Wa._,hlng'ton. EX:; 20202-457I.

Le_ed for ca.uz.e of Oelaul: a_d No_k:_ _.a._. l_c_uda the _Oem_t"K:a_k_ r'_Jm, b_r(s) _ _ao_ _l_ct_J 8. Where the appl_r..artt _ un.a_e to certify to a."ty of the gr_L :ilalemen_ In lhI:s cerlifJc._l_n, he or :_he _h41Jl alla_3ft an A,_ the dt.'yeu'lhortze<:l r'_prw._em_'e of the appnc_l. I herel_ ,:::_w.tl_ _ the app_W::_rn wle oorr, p.b' _ the ab<_,,e cert.t_W:at],or_.

3, DRUG-FREE WORKPLACE (C-,RANTE,ES o_ _ _NC_WO*JALS) As required b_ the [)Pug-Free Work::pJace A_::_ of 1988. and N._E OF xPgU_: _p_err_e_ed _ 34 CFI=I P_-t 85. SL,_:_I F. t_ _ees. =:_ defined "' 34 CFR P'_t 85, SecJor_ 85.605 and 8S.S _0 - A.,"TI"_ =N:)p_k:=u'_ certti_ L_I It will or will c:or_lnu.e Io provk_ a Wichita State University dpug-h"ee wgr'xpi_c_ by:. PR/AWARD NUMBER A,/_0_ PROJECT KAME (a) P1._U3J_r.,g a :l_llem_r_. n, olil'y_g a_ye,e.s l_%al lhe Ul'_awtuI rr_i.dac'ture, dl_rlbulbn, dl:s:p_n_Jng, pos.s.e._on, or use of a Tailplane Icing Prosram - Phase II oonlrolh_d _ut;_l_u'_c_ b pro_I_led In :i'_ gray, tee TM ww.X_lxc_ e.,..,d v_aC_r'_ the ac:IIof'_ I_I wilt be, la_(en against employees tar Gerald D. Loper, Assoc, VP for Research PRINTED NAME AND TITLE OF AUTHORIZED (b) E._I:_b_r_ _ oo-.g_r_ drug-tree awareness program Io I,_on'n e,'np k:_,ee._ a=bout-- _) "r_ c_-_rs c_ drug _ _ the _ce: 2) The grantee's po_cy ot maJr_alnlng a drug-I,'e'e _; (3) Any avalL_bhe drug Cour-3ellng. m_llffalk_n, _ en_oyee Sg u -, a._a_ce p_<jr&rT_: and

R R E AT E

(4) The p_n.a/ll_: lh_ may be lmpo_ upon ern_loye_ for drug

DATE ? / /

id_z,e v_olallon,_ occ_Jrdr)g In lhe wo_,_: ((c) Making It a mq_Ir_rr_nt _ ead'l em, p4oyee to be enlarged In ED 80.-0013 It'll' p.e#orrn._,l_ce ot the green( be given a copy ol the $_ale.n'_nl r_<:1_JW_d by p._r_gr-aph (a): Idal Notl_IrKj the employee In th.e slaterner_ required by paragraph mat. as a c_ndi_{on of employm.ent under the grant. Ihe employee wl_.

(I) Abide by lhe Iert'n_ ot the st=em.er_: (2) Notify the employer In wrtllng ol h_ or Per c._nvlcHon lot a E-1