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Wind-Tunnel Tests of a 0.182-Scale Model of an F4U-1 Airplane with External StoresTests were made in the Langley 7- by 10-foot tunnel on a 0.182-scale model of an F4U-1 airplane with external stores. This paper is concerned mainly with presenting the data obtained in this investigation and with a comparison of some of these data with flight-test results determining the feasibility of estimating flight buffet Mach number from tunnel data. The results of this investigation indicate that the incremental drag coefficient due to external stores may be used to estimate the maximum Mach number that the F4U-1 airplane may reach in flight when it is equipped with external stores. This estimation is conservative for the five configurations investigated by mounts varying from 0 to 10 percent of the flight limit Mach number. The free-stream tunnel Mach number corresponding to sonic flow over the lower surface of the wing in the region of the store is a good indication of the lower limit of buffet in flight of the F4U-1 airplane when equipped with external stores. The fluctuations of total pressure over the horizontal tail are not sufficiently large (maximum of 1 percent q(sub o) to cause buffeting of the airplane.
Document ID
20090022392
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Silvers, H. Norman (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Spreemann, Kenneth P. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 24, 2013
Publication Date
June 5, 1947
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NACA-RM-SL7E20
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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