Accession Number : AD0825505

Title :   OPTIMUM AIRFOILS AT MODERATE SUPERSONIC SPEEDS. PART 2. MINIMUM DRAG,

Corporate Author : RICE UNIV HOUSTON TX AERO-ASTRONAUTICS GROUP

Personal Author(s) : Miele, Angelo ; Heideman, John C.

Report Date : 1968

Pagination or Media Count : 19

Abstract : Minimum drag airfoils at moderate supersonic speeds are determined using second-order theory. Two cases are investigated under the assumption that the length is prescribed: (a) given thickness and (b) given enclosed area. If the thickness is given, the minimum drag airfoil is a diamond shape. If the enclosed area is given, the minimum drag airfoil is biconvex. In both cases, the maximum thickness occurs in the rear half of the airfoil; while, if the linear theory is employed, it occurs exactly at midchord. (Author)

Descriptors :   (*SUPERSONIC AIRFOILS, OPTIMIZATION), LIFT, DRAG, ANGLE OF ATTACK, TWO DIMENSIONAL FLOW, SLENDER BODIES, DISTRIBUTION, PRESSURE, SKIN FRICTION, THICKNESS, THEORY, SUPERSONIC CHARACTERISTICS.

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE