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  • AIRCRAFT STABILITY AND CONTROL  (2)
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  • 1
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    Transonic stability and control of aircraft using CFD methods (1988)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Implementation 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.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 88-4374 , AIAA Atmospheric Flight Mechanics Conference; Aug 15, 1988 - Aug 17, 1988; Minneapolis, MN; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Experimental flutter boundaries with unsteady pressure distributions for the NACA 0012 Benchmark Model (1991)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The Structural Dynamics Division at NASA Langley Research Center has started a wind tunnel activity referred to as the Benchmark Models Program. The primary objective of the program is to acquire test data that will be useful for developing and evaluating aeroelastic type CFD codes currently in use of under development. This paper describes the progress achieved in testing the first model in the Benchmark Models Program. Experimental flutter boundaries are presented for a rigid semispan model (NACA 0012 airfoil section) mounted on a flexible mount system. Also, steady and unsteady pressure measurements taken at the flutter condition are presented. The pressure data were acquired over the entire model chord located at the 60 percent span station.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 91-1010 , AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; Apr 08, 1991 - Apr 10, 1991; Baltimore, MD; United States
    Format: text
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    NASA TECHNICAL REPORTS
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