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.
Transonic wind-tunnel tests of error-compensated static-pressure probe
NASA -- Tech Notes
1961
15 pages
Report
English
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Wind-tunnel tests of seven static-pressure probes at transonic speeds
Engineering Index Backfile | 1961