Transonic Wind Tunnel Tests of an Error Compensated Static Pressure Probe

摘要

Pressure-error characteristics of a self-rotating static-pressure probe mounted on the nose of a missile body were determined at Mach numbers from 0.30 to 1.08 and at angles of attack from -2.7 deg to 15.3 deg. Results showed that at a Mach number of 1.00, the static-pressure error decreased from 3.5 percent to 0.8 percent of the free-stream static pressure as a result of a change in the orifice location from 0.15 maximum missile diameter to 0.20 maximum missile diameter forward of the missile nose. Although compensation for errors due to angles of attack up to 15.3 deg was maintained at Mach numbers from M = 0.30 to M = 0.50, there was an increase in error with an increase in angle of attack for Mach numbers between M = 0.50 and M = 1.08.