Some Remarks on an Approximate Method of Estimating the Wave Drag Due to Thickness at Supersonic Speeds of Three-Dimensional Wings With Arbitrary Profile
Abstract
A semi empirical profile-correction factor is discussed which enables the estimation of the wave drag due to thickness at supersonic speeds for three-dimensional wings with arbitrary airfoil section (subject to the restrictions of thin-airfoil theory) through use of previously calculated drag coefficients. Application of the proposed correction factor to the known drag coefficients of some rhombic-profile wings yielded estimates for the drag coefficients of parabolic-arc-profile wings that were in good agreement with theoretically calculated values. It is expected that satisfactory estimates can be obtained for many combinations of plan form and profile by judicious use of-the proposed profile correction, especially at speeds for which the wing leading edge is supersonic.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1952
- Accession Number
- ADA380436
Entities
People
- Kenneth Margolis
Organizations
- National Aeronautics and Space Administration