In parallel with the research and development conducted by the National Aerospace Laboratory (NAL) on the experimental aircraft 'ASKA', a short takeoff and landing (STOL)-Computer Aided Design (CAD) program for four-engine upper surface blowing (USB) aircraft was developed and refined. This led to the present study which modified the existing four-engine USB semi-span model into a twin-engine model and subsequently conducted low-speed wind tunnel tests. Resultant aerodynamic characteristics of the numerous aerodynamic elements included in this model are described.
Wind Tunnel Investigation of a Twin-Engine Jet Transport Semi-Span Model with Upper Surface Blown Jet Flap
1991
49 pages
Report
No indication
English