OPTIMUM AIRFOILS AT MODERATE SUPERSONIC SPEEDS. PART 3. MAXIMUM LIFT-TO-DRAG RATIO FOR GIVEN THICKNESS,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1968
- Accession Number
- AD0826494
Entities
People
- Angelo Miele
- John N. Damoulakis
Organizations
- Rice University