Pressure Distributions on a Delta Wing - Horizontal Stabilizer Combination at Mach Numbers from 0.3 to 2.9. volume 12. Vertical Tail Net Chordwise Pressure Distributions and Isobars.
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 vertical tail net chordwise pressure distributions and isobars showing the effect of sideslip and rudder deflections.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 15, 1972
- Accession Number
- AD0903841
Entities
People
- James D. Knittel
- Johan P. Moulijn
- Marjorie E. Manro
Organizations
- Boeing