Accession Number:

ADA626170

Title:

HIFiRE-1 Turbulent Shock Boundary Layer Interaction - Flight Data and Computations (Postprint)

Descriptive Note:

Conference paper

Corporate Author:

AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH AEROSPACE SYSTEMS DIRECTORATE

Personal Author(s):

Report Date:

2015-06-01

Pagination or Media Count:

14.0

Abstract:

The Hypersonic International Flight Research Experimentation HIFiRE program is a hypersonic flight test program executed by the Air Force Research Laboratory AFRL and Australian Defence Science and Technology Organisation DSTO. This flight contained a cylinder-flare induced shock boundary layer interaction SBLI. Computations of the interaction were conducted for a number of times during the ascent. The DPLR code used for predictions was calibrated against ground test data prior to exercising the code at flight conditions. Generally, the computations predicted the upstream influence and interaction pressures very well. Plateau pressures on the cylinder were predicted well at all conditions. Although the experimental heat transfer showed a large amount of scatter, especially at low heating levels, the measured heat transfer agreed well with computations. The primary discrepancy between the experiment and computation occurred in the pressures measured on the flare during second stage burn. Measured pressures exhibited large overshoots late in the second stage burn, the mechanism of which is unknown. The good agreement between flight measurements and CFD helps validate the philosophy of calibrating CFD against ground test, prior to exercising it at flight conditions.

Subject Categories:

  • Military Aircraft Operations
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE