Accession Number:

ADA137052

Title:

Analysis of Transonic Shock Induced Separated Flow Including Normal Pressure Gradients.

Descriptive Note:

Final rept. Apr 82-31 Aug 83,

Corporate Author:

UNITED TECHNOLOGIES RESEARCH CENTER EAST HARTFORD CT

Personal Author(s):

Report Date:

1983-10-01

Pagination or Media Count:

108.0

Abstract:

An analysis based on a two-layer interaction model is presented for the prediction of transonic shock-wave, boundary-layer interaction with emphasis on turbulent separated flow. In this analysis finite difference techniques are used to solve the viscous layer equations, expressed in a defect form, and the stream function-vorticity representation of the inviscid flow. A global technique is used to iteratively solve these coupled sets of equations. Normal pressure gradients and imbedded shock effects are included in the analysis. Two major conclusions can be drawn from the present work First, favorable comparisons obtained with the separated data of Kooi Mach no. 1.4 demonstrate that the present analysis is capable of accurately resolving many of the transonic shock-wave, boundary-layer interaction. Second, these results show that, for transonic shock induced separation, the effect of displacement thickness interaction dominates over that produced by imbedded shock effects and normal pressure gradients. Calculations made with a modified algebraic turbulence model demonstrate that for separated cases the computed results are more sensitive to the turbulence model than to whether or not normal pressure gradients are included.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE