Force measurements at subsonic, transonic, and supersonic Mach numbers were conducted to determine the infuence of airfoil thickness and shape on normal force and pitching moment of slender wings. Both wings, a rectangular and a clipped delta wing, had hexagonal wing sections. In addition to the variation of wing thickness, different angles of the wedge-like edges and rounded edges were investigated. The tests were performed in the trisonic wind tunnel at Mach numbers between 0.5 and 4. In supersonic flow the angle of attack varied from -10 to 90 deg, but was often limited to a lower value because of model blockage.
Wind Tunnel Tests of the Influence of Airfoil-Thickness on Normal Force and Pitching Moment of Two Slender Wings at Transonic and Supersonic Mach Numbers
1987
167 pages
Report
Keine Angabe
Englisch