Accession Number : AD0826494
Title : OPTIMUM AIRFOILS AT MODERATE SUPERSONIC SPEEDS. PART 3. MAXIMUM LIFT-TO-DRAG RATIO FOR GIVEN THICKNESS,
Corporate Author : RICE UNIV HOUSTON TX AERO-ASTRONAUTICS GROUP
Personal Author(s) : Miele, Angelo ; Damoulakis, John N.
Report Date : 1968
Pagination or Media Count : 22
Abstract : Maximum lift-to-drag ratio airfoils at moderate supersonic speeds are determined using second-order theory. The case of given length and thickness is investigated, and the optimum airfoil is found to be a diamond shape. The maximum thickness occurs in the rear half of the airfoil; while, if the linear theory is employed, it occurs exactly at midchord. The upper portion of the airfoil is thicker than the lower portion; while, if linear theory is employed, the upper and lower thicknesses are identical. (Author)
Descriptors : (*AIRFOILS, SUPERSONIC CHARACTERISTICS), LIFT, DRAG, OPTIMIZATION, THICKNESS, ANGLE OF ATTACK, EQUATIONS OF MOTION, TWO DIMENSIONAL FLOW, AERODYNAMIC CONFIGURATIONS, SKIN FRICTION.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE