DID YOU KNOW? DTIC has over 3.5 million final reports on DoD funded research, development, test, and evaluation activities available to our registered users. Click
HERE to register or log in.
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
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.
Distribution Statement:
APPROVED FOR PUBLIC RELEASE