Accession Number:

ADA093739

Title:

Interference on a Model Afterbody from Downstream Support Hardware at Transonic Mach Numbers

Descriptive Note:

Final rept. 27 Jun-2 Jul 1979

Corporate Author:

ARO INC ARNOLD AFS TN

Personal Author(s):

Report Date:

1981-01-01

Pagination or Media Count:

51.0

Abstract:

An experimental program was conducted to parametrically study the interference on an afterbody model that would be produced by the aft-support blade used with a wingtip support system. Geometric variables included the blade axial location, thickness, span, chord, and leading- and trailing-edge contours. Data were obtained over the Mach number range from 0.6 to 1.2 with the model at zero angle of attack. Interference was evaluated by comparing afterbody drag from a reference configuration, which had the aft-support blade removed, to the various configurations with a blade installed. A reasonable correlation of the blade interference effects on the afterbody drag coefficient was obtained, which included the influence of support blade axial position and blockage. Decreasing blade leading-edge bluntness by a factor of two resulted in a significant reduction of interference in the Mach number range from 0.9 to 1.1. Significantly greater interference was measured without jet flow than with jet flow. It is shown that a Euler equation computer code is a useful tool for the design of minimum interference support systems.

Subject Categories:

  • Aerodynamics
  • Attack and Fighter Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE