Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9 Volume 8. Wing Chordwise Pressure Distributions, Effects of: Nacelles, Flaps, Spoilers, Sideslip, and Reynolds Number. Part 1.
Abstract
This report presents the results of wind tunnel pressure distribution measurements made on a model of the Boeing supersonic transport configuration during design of the prototype airplanes. This volume contains upper and lower surface chordwise pressure distributions illustrating the effects of nacelles (including various types of simulated engine failure), flaps, spoilers, sideslip and Reynolds number.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 15, 1972
- Accession Number
- AD0903836
Entities
People
- James D. Knittel
- Johan P. Moulijn
- Marjorie E. Manro
Organizations
- Boeing