Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. Volume 1. Summary Report.
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. The 0.027 scale model of the B2707-300 was tested in the Ames Unitary Wind Tunnels and in the Ames 12-Foot Pressure Tunnel. Additional horizontal stabilizer pressure measurements were made in the Boeing Transonic Wind Tunnel. Pressure measurements were obtained using more than 1000 individual orifices. Tests covered the complete operating range of the airplane from Mach numbers of 0.3 to 2.9. The data include the effects of Mach number, angles of attack and sideslip, control surface deflection, and nacelle interference. This volume contains a complete description of the model and test program, and a summary of the data contained in volumes 2 through 13. In addition, it contains a review of the SST design experience, particularly in the use of the pressure measurements, and a description of pressure data available from earlier variable-wing-sweep pressure model tests.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 15, 1972
- Accession Number
- AD0903828
Entities
People
- James D. Knittel
- Johan P. Moulijn
- Marjorie E. Manro
Organizations
- Boeing