Accession Number:

ADA023354

Title:

An Analytic and Experimental Study of the Effects of Splitter Plate Position on the Trailing Edge Modifications of a Cambered Circulation Controlled Elliptical Airfoil

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1975-12-01

Pagination or Media Count:

87.0

Abstract:

Wind tunnel tests were conducted to determine the effects of splitter plate position on trailing edge modifications of a circulation controlled airfoil. Analytic studies were conducted to determine the feasibility of using a potential flow computer program to predict the results of the wind tunnel tests. The airfoil model was elliptical in shape, 20 percent thick, and had five percent camber. It employed a blowing slot for circulation control and a splitter plate for reduction in mixing losses. Modifications included slot positions on the upper surface of 96 and 97 percent chord, slot angles of 5 and -33 degrees, circular and elliptic aft contours, and splitter plate positions on the lower surface of 99 and 95.3 percent chord. Tests were conducted at a Reynolds number of 740 thousand and blowing momentum coefficients of zero and 0. 03.

Subject Categories:

  • Aerodynamics
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE