Wing-Body Interference at Supersonic Speeds With an Application to Combinations With Rectangular Wings
Abstract
An exact theoretical method is developed that permits the determination of the pressure field of a wing-body combination having a circular body and a wing with supersonic leading and trailing edges. Detailed calculations have been performed for wing-body combinations composed of rectangular wings mounted at incidence on bodies at zero angle of attack for effective chord-radius ratios of 4 or less. For large effective chord-radius ratios some asymptotic results have been obtained. It was determined that for the family of combinations having an effective chord- radius ratio of 4 the area of the wing blanketed by the body does not generate any lift itself but rather acts to support the lift generated by the exposed wing, and that the body is less than 50 percent effective in reflecting lift back to the wing. For chord-radius ratios less than 4, the relative amount of reflection increases.
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1952
- Accession Number
- ADA380438
Entities
People
- Jack N. Nielsen
- William C. Pitts
Organizations
- National Aeronautics and Space Administration