Accession Number:

ADB805395

Title:

The Calculation of Span Load Distribution on Swept-Back Wings

Descriptive Note:

Technical note

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMIN LANGLEY RESEARCH CENTER HAMPTON VA

Personal Author(s):

Report Date:

1941-12-01

Pagination or Media Count:

31.0

Abstract:

Method used was to replace wing with a bound vortex at quarter chord line and to calculate downwash caused by system of bound and trailing vortices to conform at three-quarter-chord line to slope of flat-plate wing surface. Results are given for constant-chord and 51 tapered plan forms for swept-back engine of 0, 30, and 45 deg and for aspect ratios 3, 6, and 9. Some comments on stalling of swept-back wings are included. Swept-back wing will stall first at tips and at lower angle of attack than a corresponding swept wing.

Subject Categories:

  • Aerodynamics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE