Pressure error characteristics of self-rotating static pressure probe mounted on nose of missile body were determined at 0.30 to 1.08 Mach and at angles of attack from -2.7 to 15.3°; at Mach 1.00, static pressure error decreased from 3.5 to 0.8% of free stream static pressure as result of change in orifice location from 0.15 to 0.20 maximum missile diameter forward of missile nose.


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    Title :

    Transonic wind-tunnel tests of error-compensated static-pressure probe


    Additional title:

    NASA -- Tech Notes


    Contributors:


    Publication date :

    1961


    Size :

    15 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English