Document
LANN WING DESIGN
George C. Firth
Lockheed-Georgia Company
Marietta, Georgia
The LANN wing is the result of a joint effort between Lockheed, the Air Force,
NASA, and the Netherlands to measure unsteady pressures at transonic speeds. It is
a moderate-aspect-ratio (8) transport wing configuration. The wing was machined
from NITRONIC 40 and has Q-percent-thick supercritical airfoil sections. The wing
has a semispan 1 m in length, a root chord of 0.361 m, a tip chord of Oo144 m, and
a planform area of 0.25 m . The wing has a l/4-chord sweep angle of 25 and a linear
twist from root to tip of 4.8O.
Static and oscillatory pressures were measured on the LANN wing in the high-
speed tunnel at NLR (the national aerospace research organization) in the Netherlands
in December 1981 using the NLR-developed "Matched Tubing Technique." Measurements
were made for M, from 0.62 to 0.95 at angles of attack from -0.4O to +6O. The
design condition for the wing is for a C of 0.53 at a Mach number of 0.82. The
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data from these tests will be used in de ining the test boundary in the NTF. The
instrumentation used at NLR is not appropriate for the NTF tests and-will be com-
pletely replaced after the wing has been received at Langley.
The data from this wing will be the first unsteady wind tunnel measurements
made at realistic Reynolds numbers, and the primary objective of the tests will be
to determine, which as much precision as possible, what the effects of Reynolds
number are on the unsteady pressure of a wing ocsillating in pitch.
LANN WING
Oscillating Unsteady Pressure Wing
CONFIGURATION CONFIGURATION VARIABLES t/c = 0.12 o Aileron deflection AC = 25' o Engine nacelle SEMISPAN = 1 m 0 Wing-tip fins TEST VARIABLES o M = .6, .7, .76, .82, .85, .95 0 CL = .3, .5, .7 o Re = 6 x lo6 -- 60 x lo6 o Reduced frequency 0 to .2 o B. L. transition fixing EXISTING KASJRWENT CHORDS 82.5 452 sm MEASUREMENTS o 5 Component strain gage balance o Unsteady wing pressures (200) TEST OBJECTIVES 0 Wing temperatures (15) o Reynolds No. effects on in-phase and out-of-phase 0 Wing accelerometers (9) aerodynamic forces and moments o Wing root buffet gage o Shock travel, flow separation, and buffet o Static deformation o NTF-NLR HST-Lockheed CFF data comparison
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