Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 13. Body, Nacelles, and Leading and Trailing Edge Flap Load Distributions.
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 section characteristics of the body, nacelles, and wing leading and trailing edge flaps and total integrated nacelle coefficients.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 15, 1972
- Accession Number
- AD0903842
Entities
People
- James D. Knittel
- Johan P. Moulijn
- Marjorie E. Manro
Organizations
- Boeing