A data reduction method has been developed and tested for a high frequency angle
probe. The angle probe is designed for unsteady aerodynamic measurements in
transonic cryogenic wind tunnels. The probe measures time-resolved total pressure,
static pressure, angle of attack, and yaw angle from readings of four pressure
transducers. The unique feature of this probe, as compared to a conventional multi-hole
directional probe, is that the four high frequency response silicon pressure transducers
are mounted flush on the probe tip. The data reduction method is basically an interpolation
routine of calibration curves. The calibration curves consist of experimentally
determined non-dimensional flow coefficients.
Two experiments were conducted to test the probe and the data reduction method.
The first experiment tested the angle probe in a Karman vortex street shed from a cylinder.
In the second experiment, the angle probe was placed in an open air jet with an
exit Mach number of 0.42. Plots of the time-resolved measurements and the Fast
Fourier Transform analysis were made for each test.
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