Publication Date:
2019-07-13
Description:
A data reduction technique applicable to constant temperature hot film and hot wire probes is presented which is used to determine flow angle and mass flow rate in an unknown flow field over a wide range of flow conditions at supersonic and hypersonic velocities. The technique virtually eliminates the effect of Reynolds number on a probe's flow angle sensitivity. Methods for extrapolating a limited amount of mass flow rate calibration data to include the range of mass flow rate encountered in an experiment are also given. This technique has been applied to data obtained using a hot film probe during surveys in the leeside flow field of a space shuttle orbiter configuration.
Keywords:
INSTRUMENTATION AND PHOTOGRAPHY
Type:
AIAA PAPER 78-794
,
Aerodynamic Testing Conference; Apr 19, 1978 - Apr 21, 1978; San Diego, CA
Format:
text
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