Wedge and conical shaped probes for the measurement of free-stream flow quantities at supersonic speeds have been tested in both wind tunnel and flight. These probes have improved capabilities over similar ones used in the past. Through the use of miniature pressure sensors, that are located inside the probes, they are able to provide instantaneous measurements of a time-varying environment. Detailed herein are the results of the tests in NASA Langley Researcher Center s Unitary Plan Wind Tunnel (UPWT) at Mach numbers of 1.6, 1.8 and 2.0, as well as flight tests carried out at the NASA Dryden Flight Research Center (DFRC) on its F-15 aircraft up to Mach numbers of 1.9. In the flight tests the probes were attached to a fixture on the underside of the F-15 fuselage. Problems controlling the velocity of the flow through the conical probe, required for accurate temperature measurements, are noted, as well as some calibration problems of the miniature pressure sensors that impact the accuracy of the measurements.


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    Title :

    Wedge and Conical Probes for the Instantaneous Measurement of Free-Stream Flow Quantities at Supersonic Speeds


    Contributors:

    Conference:

    29th AIAA Applied Aerodynamics Conference ; 2011 ; Honolulu, HI, United States


    Publication date :

    2011-06-27


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :



    Wedge and Conical Probes for the Instantaneous Measurement of Free-Stream Flow Quantities at Supersonic Speeds

    Bobbitt, P. / Maglieri, J. / Banks, D. et al. | British Library Conference Proceedings | 2011




    Supersonic conical flow

    Maslen, Stephen H | NTRS | 1952