The pressure distributions on sphericallyblunted cones, which are installed in test section as axisymmetric condition, are measured in the hypersonic flows produced with contour and conical nozzles of the NAL gun tunnel. The experimental results of pressure coefficient are successfully correlated by the blast-wave-type parameters C
p/C
conep and (θ
cθ
c2/√CD
n)/(x
n/d
n). The effect of nose bluntness on the pressure distribution of a blunted cone in inviscid hypersonic flow is clarified, by taking into account of viscous induced pressure included in the experimental results.
It is also shown that the pressure distribution on models tested in conical nozzle is appreciable difference as compared With that tested in contour nozzle, but they are in good agreement with each other according to the source flow correction method proposed in the present paper.
Detailed discussion about various effects, such as those of temperature and vibration, on pressure transducer is given for the measurement of low pressure.
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