Heat transfer effects on a subsonic delta wing

Abstract

With the advent of the "Space Shuttle" concept, it has become necessary to study the effects of heat transfer on the aerodynamic and boundary layer characteristics of a heated delta wing. Thus, a symmetrical 60° delta wing was tested up to twice freestream temperature in the Virginia Tech 6' x 6' stability wind tunnel. Summaries of the characteristics of the flow over the unheated wing and the theoretical effects of heat transfer are included. It has been found that heat transfer effects on the wing's aerodynamic characteristics are negligible at angles of attack up to one-third of the maximum lift angle. Beyond this, lift and pitching moment show a very small decrease and increase, respectively, up to maximum lift while drag increases 15 percent to 25 percent at maximum lift. Further increases in drag occur when the wing is yawed. No decrease in stalling angle of attack with heating is found for all yaw angles.