Accession Number:

ADA012824

Title:

Theoretical and Experimental Investigations of Jet Parallel to Wing in Cross Flow. Part I. Numerical Integration of Three-Dimensional Flow. Part II. Experimental-Laser Velocimeter Flow Field Investigations.

Descriptive Note:

Technical rept. 1 Mar 74-28 Feb 75,

Corporate Author:

LOCKHEED-GEORGIA CO MARIETTA FLIGHT SCIENCES DIV

Personal Author(s):

Report Date:

1975-04-30

Pagination or Media Count:

104.0

Abstract:

Theoretical and experimental analysis of jet flow parallel to a wing and in cross flow is presented. A numerical model is developed to integrate the three-dimensional flow field equations. A parabolic approximation is assumed and marginally stable solutions are obtained. It is concluded that stability problems arise because of a combination of an incomplete theoretical model and an inadequate numerical integration scheme. Turbulence parameters are obtained from laser velocimeter measurement of the flow field. Laser and surface pressure tests were conducted. Pressure tests include low and high angle of attack results of spanwise blowing over a low aspect ratio semi-span model. High angle of attack data include the effects of leading edge vortex control by spanwise blowing. Only low angle of attack data are presented for the laser flow field tests.

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE