Comparisons Of Theoretical And Experimental Pressure Distributions Over A Wing Body Model At High Supersonic Speeds

A critical comparison is presented between experimental and theoretical results for the aerodynamic characteristics of wings at supersonic flight speeds. After a brief review of supersonic wing theory and of previous results from two-dimensional pressure-distribution tests, an account is given of an NACA study of the force characteristics of three-dimensional wings at supersonic speed. Typical experimental and theoretical results are presnted for the lift, pitching-moment, and drag characteristics of several families of wings of varying plan form and section. The regions of agreement and disagreement experiment and theory are noted and discussed.

An investigation was conducted at a Mach number of 1.90 to determine spanwise pressure distribution over a wing tip in a region influenced by a sharp subsonic trailing edge. The wing section was a symmetrical wedge of 5 degrees 43 minutes total included angle in the free-stream direction. The investigation was conducted over a range of angles of attack from -10 to 10 degrees at a Reynolds number of 3,400,000 per foot.