A new type of thin-film heat transfer gauge is applied to the measurements of heat-transfer coefficients in the interaction regions of oblique shock waves and fully developed turbulent boundary layers. It has been developed for the measurement of heat flux with high spatial resolution and fast response for wind tunnels with a long flow duration. Experiments have been performed for a Mach number of 4, a total pressure of 1. 2 MPa, a wall pressure ratio of 0. 59-0. 65, a Reynolds number of (1. 3-1. 5). 10**7, and incident shock angles from 17. 8 to 22. 8 degrees. The flow fields are visualized by the Schlieren technique. Both the surface pressure distributions and the heat transfers are measured throughout theinteraction regions by scanning the shock generator parallel to the freestream. Owing to the high spatial resolution of the new sensor, complicated features of the aerodynamic heating in the interaction region are revealed.
|Number of pages||9|
|Journal||Transactions of the Japan Society for Aeronautical and Space Sciences|
|Publication status||Published - Aug 1987|
All Science Journal Classification (ASJC) codes
- Aerospace Engineering