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The measured and estimated rotary stability derivatives of the X-15 airplaneMeasurements of the rotary derivatives of the X-15 aircraft were made in several of the wind tunnels of the National Advisory Committee for Aeronautics. The speed range was from landing speed up to Mach number, 3.5. The measurements were made on the steady-state, forced-oscillation equipment. The apparatus measures the rotary derivatives during small-amplitude, single-degree-of-freedom oscillations. In this paper the results of the wind-tunnel tests are compared with the values of the rotary derivatives estimated by the available procedures. Whenever possible, the results of wind-tunnel measurements of the static forces and moments on the X-15 have been utilized in the estimation procedures to obtain lift-curve slopes and centers of pressure of the tail surfaces. In this way, at least a partial account is taken of the effects of the fuselage and wing downwash and pressure field on the tail surfaces.
Document ID
19930092384
Acquisition Source
Legacy CDMS
Document Type
None
Authors
Tinling, Bruce
(North American Aviation, Inc)
Surber, True
Tunnell, Phillips J
Lopez, Armando
Date Acquired
August 15, 2013
Publication Date
July 30, 1958
Accession Number
93R21674
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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