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Error in Airspeed Measurement Due to Static-Pressure Field Ahead of the Wing Tip of a Swept-Wing Airplane Model at Transonic SpeedsAs part of a study of means of airspeed measurement at transonic speeds the use of static orifices located ahead of the wing tip has been investigated for possible application to service or research airspeed installations. The local static pressure and local Mach number have been measured at a distance of 1 tip chord ahead of the wing tip of a model of a swept-wing fighter airplane at true Mach numbers between 0.7 and 1.08 by the NACA wing-flow method. All measurements were made at or near zero lift. The local Mach number was found to be essentially equal to the true Mach numbers less than about 0.90. The local Mach number was found to be about 0.97 at a true Mach number of 0.95, and to be about 1.04 at a true Mach number of 1.08. The local Mach number provided a reasonable sensitive measure of true Mach number except for a restricted region near a true Mach number of 1.0 where the local Mach number did not change appreciably with true Mach number. The linear theory was found to predict qualitatively the effect of the fuselage on the static pressure ahead of the wing time but gave a reasonable prediction of the effect of the wing on the static pressure only at Mach numbers below 0.95.
Document ID
20090012111
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Danforth, Edward C.B.
O'Bryan, Thomas C.
Date Acquired
August 24, 2013
Publication Date
March 1, 1951
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-RM-L50L28
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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