Accession Number:

AD0261702

Title:

TRANSONIC WIND-TUNNEL TESTS OF AN ERROR-COMPENSATED STATIC-PRESSURE PROBE

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

Report Date:

1961-08-01

Pagination or Media Count:

1.0

Abstract:

An investigation of the pressure-sensing characteristics of an error-compensated static-pressure probe mounted on the nose section of a missile body has been conducted in the Langley 16-foot transonic tunnel. The probe was free to rotate about its roll axis and was equipped with a vane so that the crossflow velocity component due to angles of attack or sideslip was always alined with the probes vertical plane of symmetry. The probe was tested in five axial positions with respect to the missile nose at Mach umbers from 0.30 to 1.08 and at angles of attack from -2.7 degrees to 15.3 degrees. The test Reynolds number per foot varied from 1.79 x 10 to the 6th power to 4.05 x 10 to the 6th power. Results showed that at a Mach number of 1.00 the static-pressure error decreased from 3.5 to 0.8 of the free-stream static pressure, as a result of a change in orifice location from 0.15 maximum missile diameter to 0.20 maximum missile diameter forward of the missile nose. Although compensation for pressure-sensing errors due to angles of attack up to 15.3 was maintained at Mach numbers from M equals 0.30 to M equals 0.50, there was an increase in error with an increase in angle of attack for Mach numbers between M equals 0.50 and M equals 1.08. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE