Accession Number:

ADA610758

Title:

Stability Analysis of High-Speed Boundary-Layer Flow with Gas Injection

Descriptive Note:

Technical paper, May-Jun 2014

Corporate Author:

AIR FORCE RESEARCH LAB EDWARDS AFB CA ROCKET PROPULSION DIV

Report Date:

2014-06-01

Pagination or Media Count:

19.0

Abstract:

Stability analyses of high-speed boundary-layer flow past a 5 deg half angle sharp cone with the wall-normal injection of air through a porous strip are performed using Navier-Stokes solutions for the mean flow and linear stability theory. The configuration and free-stream parameters are chosen to be similar to the experiments, which were carried out at Caltechs T5 shock tunnel to investigate the effect of CO2 injection on laminar-turbulent transition. The analysis is focused on pure aerodynamic effects in the framework of perfect gas model. It is shown that the injection leads to destabilization of the Mack second mode in the nearfield relaxation region and its stabilization in the far-field relaxation region. To reduce the destabilization effect it was suggested to decrease the injector surface slope or use suction blowing of zero net injection. However, the eN computations showed that these modifications did not improve the injector performance in the near-filed region in general. For special cases of low injection rates in which the N-factors in the near field region are below the critical level, shaping can produce a significant stabilization in the mid- and far-field regions.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE