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High-Speed Wind-Tunnel Tests of a Twin-Fuselage Pursuit AirplaneAt the request of the Air Technical Service Command, U.S. Army Air Forces, a 0.22-scale model of a twin-fuselae pursuit airplane was built and tested at the Ames Aeronautical Laboratory. The tests of this model were made in order that the aerodynamic characteristics of the airplane, especially at high speed, might be predicted. The results shown in this report consist of force data for the model and critical Mach numbers of parts of the model as determined from pressure-distribution measurements. The results indicate that a diving tendency of the airplane can be expected at Mach numbers above 0.70 at lift co-efficients from 0 to 0.4. There is an indication that the Mach number at which the airpolane would first experience a diving tendency for lift coefficients from 0 to 0.2 can be increased if the critical speed of the radiator enclosures is increased, and the wing-fuselage-juncture fillets are improved.
Document ID
19930092695
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Wartime Report
Authors
Tkac, Victor B
Date Acquired
August 15, 2013
Publication Date
April 24, 1946
Subject Category
Aerodynamics
Report/Patent Number
NACA-WR-A-75
NACA-MR-A6D03
Accession Number
93R21985
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
WIND TUNNEL TESTS(AAL-HIGH-SPEED-16')(AMER )
FILLETS
MACH NUMBER
DIVING TESTS - NORTH AMERICAN P-82
AIRPLANES - NORTH AMERICAN P-82 (EXPERIMENTAL)
WIND TUNNEL TESTS - AAL - HIGH-SPEED(16')
AIR FLOW - DUCTS

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