SECTION AT Z = 30.00 - DELTA Z = 1.00
SECTION AT Z = 30.00 - DELTA Z = 1.00 r -25 -15 -5 15 25 X ENTER: 0-QOIT. I-NEW DEL. Z. 2-FIT ELUPSE. 3-FOURtERFlT. 4-MANUAL FTT. 5-REFRESH. 6-NEXT Z Figure 3. Terminal display: Fuselage panel corners and an elliptical fit.
SECTION AT Z = 160.00 - DELTA Z = 5.00
SECTION AT Z = 160.00 - DELTA Z = 5.00
80 -
60 -
-70 -50 -30 -10 10 30 50
ENTER: 0-OUIT. 1-NEW DEL 2. 2-F1T ELLIPSE. 3-FOURIERFIT, 4-MANUAL FIT. S-REFRESH. 6-NEXT Z a) Fuselage panel corners and elliptical f i t .
SECTION AT Z = 160.00 - DELTA Z = 5.00 0 0 © © 0 © © © © © © © © © «•-
-70 -50 -30 -10 10 30 50 70
X ANGLE- -90.- K- + 1X. J--1X. L—MOX. H--10X. R-REFRESH. F-FORWARO. B-BACK b) Start of the manual fit.
Figure 4. Terminal display: Example of a manual fit.
SECTION AT Z = 160.00 - DELTA Z = 5.00
SECTION AT Z = 160.00 - DELTA Z = 5.00 © © © © © © -70 -50 -30 -10 10 30 70 ANCLE- -45.- K- + 1X, J--1X, L- + 10X. H--10X. R-REFRESH, F-FORWARD. B-8ACK c) Continuation of the manual f i t .
SECTION AT Z = 160.00 - DELTA Z = 5.00 r
60 -
-©—®—©- -70 -50 -30 -10 10 30 50 70 X ENTER: 0-OUtT. 1-NEW DEL Z. 2-FIT ELLIPSE. 3-FOURIERFIT. 4-MANUAL FIT. 5-REFRESH. 6-NEXT 2 d) Competed manual fit.
Figure 4. Terminal display: Example of a manual fit (concluded), Figure 5. Panel representation of the wake displacement body.
£ S H E UC 0 P fr^TuI E L AGE a= 5.0 deg >u= 0.05 a= 5.0 deg HELICOPTER FUSELAGE M= 0.05 Figure 6. Example of the output of ¥ABPLOT.
HELICOPTER FUSELAGE AIRLOADS 0.08 — LIFT C =.00780 ---DRAG T 5-JUL-88 SIDE FORCE 0.06 o: X 0.04 0.02
o
o:
o
0.00 -0.02
60 120 180 240 300 360
BLADE AZIMUTH a) Aerodynamic forces on the fuselage.
FUSELAGE-INDUCED VELOCITIES AT ROTOR M=0.05 r/R=0.75 CO
CL
o
-1
o
_J LJ RADIAL VELOCITY, BODY INDUCED.
-3 TANGENTIAL VELOCITY, BODY INDU AXIAL VELOCITY, BODY INDUCED, -5 60 120 180 240
300 360
BLADE AZIMUTH b) Fuselage-induced velocities at the rotor.
Figure 7. Example of the output of PLOTWAB.
BLADE CIRCULATION, FSQ/S
o t
. . /11. . , .
Azimuth, deg 36O c) Contour plot of the blade bound circulation.
Figure 7. Example of the output of PLOTVAB (concluded).
VELOCITY AT HELICOPTER FUSELAGE PANEL 1.5 Q_ CO
1.0
o
0.5 X (lateral) M=.050 PANEL 121 Y (Vertical) Z (Longitudinal) B O -0.5
o
60 120 180 240 300 360
BLADE AZIMUTH a) Time history of the velocity at a fuselage panel.
PRESSURE ALONG HELICOPTER FUSELAGE BODYLINE 8r O LJ CO CO -4 LJ o: Q_
-8
-12
0.0 0.4 0.8 1.2 1.6 2.0
DISTANCE, z/R
b) Pressure along a fuselage bodyline.
Figure 8. Example of the output of CVFPLT.
NASA
Report Documentation Page
Nlaional Ae^onautcs ana Space A 1. Report No. 2. Government Accession No. 3. Recipient's Catalog No.
NASA CR-181701 4. Title and Subtitle 5. Report Date Program User's Manual for an Unsteady Helicopter August^ 1988 ' Rotor-Fuselage Aerodynamic Analysis 6. Performing Organization Code 7. Author(s) 8. Performing Organization Report No.
Peter F. Lorber R88-956977-14 10. Work Unit No.
505-61-51-10 9. Performing Organization Name and Address 11. Contract or Grant No.
United Technologies Research Center NAS1-17469 East Hartford, CT 06108 13. Type of Report and Period Covered 12. Sponsoring Agency Name and Address Contractor Report National Aeronautics and Space Administration 14. Sponsoring Agency Code >£angley- Res,ear-ch -Center x Ramp ton, ..VA- 2-3665-5225 15. Supplementary Notes ^Langley Technical Monitor: John C. Wilson 16. Abstract The Rotor-Fuselage Analysis is a method of calculating the aerodynamic interaction between a helicopter rotor and fuselage. This manual describes the structure and operation of the computer programs that make up the Rotor-Fuselage Analysis, the programs that prepare the input and the programs that display the output.
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