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Review of Aircraft Altitude Errors Due to Static-Pressure Source and Description of Nose-Boom Installations for Aerodynamic Compensation of ErrorA brief review of airplane altitude errors due to typical pressure installations at the fuselage nose, the wing tip, and the vertical fins is presented. A static-pressure tube designed to compensate for the position errors of fuselage-nose installations in the subsonic speed range is described. This type of tube has an ogival nose shape with the static-pressure orifices located in the low-pressure region near the tip. The results of wind-tunnel tests of these compensated tubes at two distances ahead of a model of an aircraft showed the position errors to be compensated to within 1/2 percent of the static pressure through a Mach number range up to about 1.0. This accuracy of sensing free-stream static pressure was extended up to a Mach number of about 1.15 by use of an orifice arrangement for producing approximate free-stream pressures at supersonic speeds and induced pressures for compensation of error at subsonic speeds.
Document ID
19980228036
Acquisition Source
Headquarters
Document Type
Other - NASA Memorandum (MEMO)
Authors
Gracey, William (NASA Langley Research Center Hampton, VA United States)
Ritchie, Virgil S. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1959
Subject Category
Aerodynamics
Report/Patent Number
NASA-MEMO-5-10-59L
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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