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Transonic stability and control of aircraft using CFD methodsImplementation of a capability to calculate longitudinal short-period response in the CAP-TSD (Computational Aeroelasticity Program - Transonic Small Disturbance) finite-difference code is described. The code, developed recently at the NASA Langley Research Center, is capable of solving steady and unsteady flows about complete aircraft configurations and is used primarily for aeroelastic calculations in the critical transonic speed range. The longitudinal short-period equations of motion in state-space form have been coupled to the time-accurate lift and moment calculated by the program. Transient responses to an elevator pulse for free-flying aircraft demonstrate the new capability. A trim routine is also added to the code to obtain trim automatically during steady-state flow field convergence. Stability and control derivatives are estimated from the calculated transient response by a maximum likelihood estimation program. Results for a fighter configuration and a general aviation configuration are presented to assess the capability.
Document ID
19880063385
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Vinh, Lam-Son
(NASA Langley Research Center; George Washington University Hampton, VA, United States)
Edwards, John W.
(NASA Langley Research Center Hampton, VA, United States)
Seidel, David A.
(NASA Langley Research Center Hampton, VA, United States)
Batina, John T.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 88-4374
Meeting Information
Meeting: AIAA Atmospheric Flight Mechanics Conference
Location: Minneapolis, MN
Country: United States
Start Date: August 15, 1988
End Date: August 17, 1988
Accession Number
88A50612
Distribution Limits
Public
Copyright
Other

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