Accession Number:

AD0767363

Title:

STOL Tactical Aircraft Investigation. Volume 4. Wind Tunnel Data Analysis

Descriptive Note:

Final rept. 7 Jun 1971-31 Jan 1973

Corporate Author:

GENERAL DYNAMICS SAN DIEGO CA CONVAIR AEROSPACE DIV

Report Date:

1973-05-01

Pagination or Media Count:

406.0

Abstract:

Force and rake information measured during 1087 hours of low speed wind tunnel testing conducted by Convair Aerospace are summarized. Over 2730 data runs were generated on 242 major configuration variables that covered the following liftpropulsion concepts mechanical flaps plus vectored thrust, externally blown flaps, and internally blown flaps. Lift data was reduced into three basic terms power-on to power-off lift curve slope ratio, trailing edge flap lift increment at alpha zero degrees, and maximum lift coefficient increment due to the application of power. These relationships were evaluated as a function of blowing momentum coefficient and correlated for the effects of configurational variations wing planform, leading and trailing edges, and nacelle location. Drag data was reduced into the form of induced drag factor, minimum profile drag, thrust recovery and then analyzed as a function of blowing momentum coefficient. The pitching moment data analysis compares the flap pitching moment increment among the various configurations.

Subject Categories:

  • VSTOL

Distribution Statement:

APPROVED FOR PUBLIC RELEASE