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Estimation of dynamic stability parameters from drop model flight testsA recent NASA application of a remotely-piloted drop model to studies of the high angle-of-attack and spinning characteristics of a fighter configuration has provided an opportunity to evaluate and develop parameter estimation methods for the complex aerodynamic environment associated with high angles of attack. The paper discusses the overall drop model operation including descriptions of the model, instrumentation, launch and recovery operations, piloting concept, and parameter identification methods used. Static and dynamic stability derivatives were obtained for an angle-of-attack range from -20 deg to 53 deg. The results of the study indicated that the variations of the estimates with angle of attack were consistent for most of the static derivatives, and the effects of configuration modifications to the model (such as nose strakes) were apparent in the static derivative estimates. The dynamic derivatives exhibited greater uncertainty levels than the static derivatives, possibly due to nonlinear aerodynamics, model response characteristics, or additional derivatives.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Chambers, J. R.
(NASA Langley Research Center Hampton, Va., United States)
Iliff, K. W.
(NASA Flight Research Center Edwards, Calif., United States)
Date Acquired
August 11, 2013
Publication Date
March 1, 1981
Subject Category
Aircraft Stability And Control
Meeting Information
Meeting: Lecture Series on Dynamic Stability Parameters
Location: Moffett Field, CA
Country: US
Start Date: March 2, 1981
End Date: March 5, 1981
Sponsors: NATO, AGARD
Accession Number
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