Accession Number:

ADA192720

Title:

An Investigation of Wing Lift Augmentation with Spanwise Tip Blowing.

Descriptive Note:

Final rept. Sep 83-Oct 86,

Corporate Author:

NIELSEN ENGINEERING AND RESEARCH INC MOUNTAIN VIEW CA

Report Date:

1987-04-22

Pagination or Media Count:

256.0

Abstract:

Experimental and analytical investigations or lift augmentation on fighter type wings with wing tip blowing are described. Results of a small-scale wind tunnel test program in the NEAR, Inc. facility are presented for three wings with a wide range of tip nozzle configurations. Effects of nozzle geometry and blowing rate are described, and optimum tip nozzles are selected for further examination in a large-scale test. Results from a large scale test program in the 7- by 10-foot wind tunnel at the NASAAmes Research Center are presented for a typical fighter wing with tip blowing. Effects of tip nozzle geometry and blowing rate on lift and drag augmentation, measured pressure distributions, and flow field surveys are discussed. Keywords Lift augmentation, Numerical analysis, Wing tip blowing.

Subject Categories:

  • Attack and Fighter Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE