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High-Speed Wind-Tunnel Investigation of the Longitudinal Stability and Control Characteristics of a 0.10-Scale Model of the Grumman XF9F-2 Airplane, TED No. NACA DE301An investigation was made in the Langley high-speed 7-by 10-foot tunnel to determine the high-speed longitudinal stability end con&o1 characteristics of a 0.01-scale model of the Grumman XF9F-2 airplane in the Mach number range from 0.40 to 0.85. The results indicated that the lift and drag force breaks occurred at a Mach number of about 0.76. The aerodynamic-center position moved rearward after the force break and control position stability was present for all Mach numbers up to a Mach number of 0.80.
Document ID
20050029397
Acquisition Source
Langley Research Center
Document Type
Other - NACA Research Memorandum
Authors
Polhamus, Edward C. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
King, Thomas J., Jr. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 22, 2013
Publication Date
January 1, 1948
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-SL8K16
Report Number: NACA-RM-SL8K16
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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