Accession Number : ADA310763

Title :   Measured AEDC Tunnel B and Predicted Linear Stability Theory Transition Comparison Study for a 7-Degree Sharp Cone.

Descriptive Note : Final rept. Oct 95-Mar 96,

Corporate Author : WRIGHT LAB WRIGHT-PATTERSON AFB OH FLIGHT DYNAMICS DIRECTORATE

Personal Author(s) : Rougeux, Albert A.

PDF Url : ADA310763

Report Date : MAR 1996

Pagination or Media Count : 50

Abstract : The location of the stability region between the laminar and turbulent flow is of great importance in the design of high speed missiles and aircraft's. Heat transfer and skin friction vary greatly between laminar and turbulent, therefore, transition location is indispensable for predicting vehicle performance. The boundary layer stability of a sharp, 7-degree half angle cone with freestream Mach numbers of 6 and 8 was numerically investigated using linear stability theory computer program. Results were compared with wind tunnel tests results obtained at the AEDC Von Karman Hypersonic Tunnel B. Measured and computed frequencies agree well, indicating that linear stability theory properly describes the processes leading to transition at the AEDC Tunnel B.

Descriptors :   *AERODYNAMIC STABILITY, *BOUNDARY LAYER TRANSITION, HEAT TRANSFER, COMPUTER PROGRAMS, MATHEMATICAL MODELS, LINEAR SYSTEMS, EIGENVECTORS, TURBULENT FLOW, COMPUTATIONAL FLUID DYNAMICS, PRESSURE MEASUREMENT, TEMPERATURE GRADIENTS, WIND TUNNEL TESTS, MACH NUMBER, FREE STREAM, LAMINAR FLOW, CONICAL BODIES, PRESSURE DISTRIBUTION, REYNOLDS NUMBER, SKIN FRICTION, HOT WIRE ANEMOMETERS, BOUNDARY LAYER FLOW, HYPERSONIC FLOW, LAMINAR BOUNDARY LAYER.

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE