Accession Number : AD0834485
Title : OPTIMUM AIRFOILS AT MODERATE SUPERSONIC SPEEDS. PART 4. MAXIMUM LIFT-TO-DRAG RATIO FOR GIVEN ENCLOSED AREA,
Corporate Author : RICE UNIV HOUSTON TX AERO-ASTRONAUTICS GROUP
Personal Author(s) : Miele, Angelo ; Damoulakis, John N.
Report Date : 1968
Pagination or Media Count : 30
Abstract : Airfoils of maximum lift-to-drag ratio at moderate supersonic speeds are determined using second-order theory. The case of given length and given enclosed area is investigated, and the optimum airfoil is found to be biconvex. 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. Numerical examples show that the geometry of the optimum airfoil for M = square root of 2 is almost identical with that for M = square root of 5. (Author)
Descriptors : *SUPERSONIC CHARACTERISTICS), (*AIRFOILS, LIFT, DRAG, AERODYNAMIC CONFIGURATIONS, THICKNESS, OPTIMIZATION, MATHEMATICAL PREDICTION, SLENDER BODIES, PRESSURE, SKIN FRICTION, PROBLEM SOLVING.
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE