OPTIMUM AIRFOILS AT MODERATE SUPERSONIC SPEEDS. PART 4. MAXIMUM LIFT-TO-DRAG RATIO FOR GIVEN ENCLOSED AREA,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1968
- Accession Number
- AD0834485
Entities
People
- Angelo Miele
- John N. Damoulakis
Organizations
- Rice University