An Aerodynamic Investigation of a Forward Swept Wing

This study consisted of modeling and wind tunnel testing of a high speed, subsonic, low aspect ratio, forward swept wing with an advanced supercritical airfoil section for the purpose of determining its lift, drag, and pitching moment characteristics as compared to a similar aft swept wing. Tests were conducted at Mach numbers of 0.63 to 0.93 in the Air Force Flight Dynamics Laboratory's Trisonic Gasdynamic Facility located at Wright-Patterson Air Force Base, Ohio. Two wing configurations, forward and aft swept, were tested and compared to computer predictions provided by the Unified Subsonic-Supersonic Program (Woodward's Version B). The results indicated that the forward swept wing was capable of higher useable angles of attack while maintaining a lower drag coefficient for angles of attack below eight degrees. Wind tunnel test results are presented in graphical and tabular form for use in future design studies of similar aerodynamic configurations.