Accession Number:

AD0903836

Title:

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.

Descriptive Note:

Final rept. on Task 3,

Corporate Author:

BOEING COMMERCIAL AIRPLANE CO SEATTLE WA

Report Date:

1972-07-15

Pagination or Media Count:

401.0

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.

Subject Categories:

  • Aerodynamics
  • Transport Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE