Aerodynamic Investigation of C-141 Leading Edge Modifications for Cruise Drag Reduction--Test 2.
Final rept. Oct 78-Aug 80,
LOCKHEED-GEORGIA CO MARIETTA
Pagination or Media Count:
A wing leading edge modification for cruise drag reduction on the C-141 aircraft has been designed and wind tunnel tested. The modification was designed using a CONMIN optimizer linked to a transonic airfoil code. It was tested in the AEDC 16-Foot Transonic Facility, using a 0.044 scale C-141B model, to determine the effects of the modifications on C-141 cruise aerodynamic characteristics and wing chordwise pressure distributions. Measured chordwise pressure distributions were used for correlations with transonic theory. Force data results were analyzed to determine the effects on C-141 cruise drag, drag rise, and cruise performance. A fuel savings evaluation was made based on measured cruise performance improvements. The effects of Lockheed designed swept wing tip extensions and trailing edge anti-drag bodies were also investigated in combination with the wing leading edge modification. Author
- Transport Aircraft