A Short Static-pressure Probe Design for Supersonic Flow PDF Download
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Author: I. S. Donaldson Publisher: ISBN: Category : Languages : en Pages : 17
Book Description
Tests carried out on a short static probe at supersonic speeds between Mach numbers of 1.1 and 2.5 are described. The probe consists of a 50 deg included angle cone-cylinder having sensing holes 0.88 calibres aft of the cone-cylinder junction. The tests show that at zero incidence the probe measures a pressure (approximately independent of Mach number) of 0.793 times the local static pressure. They also show that, at up to 18 deg incidence in any pitch plane, the pressure measured is 0.763 plus or minus 0.03 times the local static pressure. For a limited Mach number range near a Mach number of 1.6, this accuracy can be maintained to incidences over 30 deg. Of particular interest is the fact that relatively small internal differences between externally identical probes appear to have a significant effect on the incidence characteristics and in some respects can improve the performance. (Author).
Author: J. Don Gray Publisher: ISBN: Category : Languages : en Pages : 43
Book Description
Pertinent facts in the literature have been examined regarding the aerodynamic characteristics of static-pressure measuring probes in order to assess the relative merits and limitations of cone-cylinder, sharp-cone, and planar (disk) probles. The effects of Mach number, angle of attack, orifice location, and Reynolds number on the inferred local pressures were all evaluated at Mach numbers up to 8. It is concluded that the planar probe and sharp-cone probe (if properly designed) are equally more accurate than the cone-cylinder probe at supersonic and hypersonic speeds. However, the cone-cylinder is judged to be superior for use at Mach numbers below 4. Details of a recommedned procedure to correct for the effects of viscous interaction (all probes) and angle of attack (planar probes only) are included. (Author).