Accession Number:

AD0903842

Title:

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.

Descriptive Note:

Final rept. on Task 3,

Corporate Author:

BOEING COMMERCIAL AIRPLANE CO SEATTLE WA

Report Date:

1972-07-15

Pagination or Media Count:

429.0

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 section characteristics of the body, nacelles, and wing leading and trailing edge flaps and total integrated nacelle coefficients.

Subject Categories:

  • Aerodynamics
  • Transport Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE