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

Personal Author(s) : Mendenhall, Michael R ; Caruso, Steven C ; Lesieutre, Daniel J ; Childs, Robert E

PDF Url : ADA192720

Report Date : 22 Apr 1987

Pagination or Media Count : 256

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 NASA/Ames 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.

Descriptors :   *LIFT, *WING TIPS, AUGMENTATION, CONFIGURATIONS, DRAG, FIGHTER AIRCRAFT, FLOW FIELDS, GEOMETRY, NOZZLES, NUMERICAL ANALYSIS, PRESSURE DISTRIBUTION, RANGE(EXTREMES), RATES, SURVEYS, WINGS, PNEUMATIC EQUIPMENT, AIR FLOW

Subject Categories : Attack and Fighter Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE