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Determination of aerodynamic parameters of a fighter airplane from flight data at high angles of attackA procedure for the estimation of airplane model structure and parameters is applied to data from a modern fighter airplane operating within an angle of attack range of 5 to 60 deg. The paper briefly describes the airplane, flight and wind tunnel data available, and the estimation method. The results presented contain basic longitudinal characteristics of the airplane and the estimates of aerodynamic parameters in the yawing-moment equations. These estimates are obtained from small and large amplitude maneuvers. Because the latter set of data was not suitable for airplane identification, some of the large amplitude maneuvers were joined together and then partitioned into subsets according to the values of angle of attack. Each subset was then analyzed as a separate data set. Most of the estimated parameters and functions are in good agreement with the wind tunnel measurements. The estimated lateral parameters in the model equations also demonstrate good prediction capabilities.
Document ID
19830060686
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Klein, V.
(Joint Institute for Advancement of Flight Sciences Hampton, VA, United States)
Batterson, J. G.
(NASA Langley Research Center Hampton, VA, United States)
Abbasy, I.
(Joint Inst. for Advancement of Flight Sciences Hampton, VA, United States)
Date Acquired
August 11, 2013
Publication Date
August 1, 1983
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 83-2066
Accession Number
83A41904
Distribution Limits
Public
Copyright
Other

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