Tests were conducted in the Langley full scale tunnel to determine the low speed aerodynamic characteristics of a large scale advanced arrow-wing supersonic transport configuration with engines mounted above the wing for upper surface blowing. Configuration variables included trailing edge flap deflection, engine jet nozzle angle, engine thrust coefficient, engine out operation, and asymmetrical trailing edge BLC for providing roll trim. Downwash measurements at the tail were obtained for different thrust coefficients, tail heights, and at two fuselage stations. (Author)
Low Speed Wind Tunnel Investigation of a Large-Scale Advanced Arrow Wing Supersonic Transport Configuration with Engines Mounted Above the Wing for Upper-Surface Blowing
1975
69 pages
Report
No indication
English