Calculations of the Supersonic Wave Drag of Nonlifting Wings with Arbitrary Sweepback and Aspect Ratio Wings Swept Behind the Mach Lines
Abstract
On basis of theory for finite swept-back wings at supersonic speeds, calculations for supersonic wave drag were made for various series of wings having thin, symmetrical, biconvex sections with untapered plan forms and various angles of sweepback and aspect ratio. Results showed that, in general, wave-drag coefficient decreased with increasing sweepback. In order to check these results, comparisons were made with results of tests of swept-back wing attached to a freely falling body. Variations of drag with Mach number and aspect ratio showed good agreement with experiments for range of Mach numbers.
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 21, 1947
- Accession Number
- ADA800858
Entities
People
- Margaret D. Swanson
- Sidney M. Harmon
Organizations
- Langley Research Center