Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 2. Comparisons of Theory and Experiment.
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 comparisons of the results of the wing and horizontal stabilizer pressure measurements with the predictions of linear potential flow theory.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 15, 1972
- Accession Number
- AD0903829
Entities
People
- James D. Knittel
- Johan P. Moulijn
- Marjorie E. Manro
Organizations
- Boeing