Accession Number : ADA011983

Title :   High Reynolds Number Transonic Testing.

Descriptive Note : Final rept. 30 Jun 71-30 Jun 74,

Corporate Author : OHIO STATE UNIV COLUMBUS AERONAUTICAL AND ASTRONAUTICAL RESEARCH LAB

Personal Author(s) : Lee,John D.

Report Date : MAY 1975

Pagination or Media Count : 43

Abstract : An experimental program was conducted to investigate the feasibility of using a pressurized blowdown wind tunnel to simulate transonic flows at flight Reynolds numbers. A 4 inch by 10 inch channel proved to be capable of supplying essentially two-dimensional flows over airfoil models; flow departure from the two-dimensional approximation occurred when shock waves terminating local flows of Mach number greater than about 1.5 caused separation of the sidewall boundary layers. Simulation of the interaction between the terminal shock wave and the model boundary layer appeared to be adequate. Comparisons with data from a larger wind tunnel indicated little or no interference in the subcritical flow range but a large and unpredictable induced attack angle.

Descriptors :   *Transonic characteristics, *Wind tunnel tests, Feasibility studies, Model tests, Airfoils, Wind tunnel models, Interactions, Two dimensional flow, Simulation, Shock waves, Flow separation, Boundary layer flow, Reynolds number, Supercritical flow

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE