Wind Tunnel Tests of a Large-Chord, Swept-Panel Model to Investigate Shock-Induced Separation Phenomena.
Final technical rept. 16 Dec 68-15 Oct 69,
LOCKHEED-GEORGIA CO MARIETTA
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The model had a chord of 3.5 feet with a streamwise airfoil section identical to that at 38.9 percent of the semispan of the C-141 wing, but had no taper or twist. Pressure distribution measurements were made through a range of angles of attack and Mach numbers for which data were available on the complete C-141 airplane from previous wind tunnel and flight tests. Fluctuating pressures at several chordwise locations near the shock were measured for a number of test conditions. Author
- Transport Aircraft