Force Tests on a Slotted Delta Wing with Varying Leading-Edge Camber at Supersonic Mach Numbers
Final rept. 20-28 Aug 1968
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
Pagination or Media Count:
Tests were conducted in a 40-in. supersonic wind tunnel on a 70-deg- sweep delta wing. A gap between the leading edge and main body was varied from a sealed condition to a nominal 0.030-in. opening for three leading edges of various camber. The aerodynamic characteristics of these configurations were obtained at Mach numbers 1.5, 2.0, and 3.0 at angles of attack from -12 to 12 deg and Reynolds numbers, based on the 10-in. model root chord, from 1,300,000 to 6,000,000. Results are presented showing the variation in liftdrag for various combinations of gap width and leading-edge camber.
- Fluid Mechanics