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  • 1
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    Steady and unsteady transonic small disturbance analysis of realistic aircraft configurations (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A transonic unsteady aerodynamic and aeroelastic code called CAP-TSD (Computational Aeroelasticity Program - Transonic Small Disturbance) was developed for application to realistic aircraft configurations. It permits the calculation of steady and unsteady flows about complete aircraft configurations for aeroelastic analysis of the flutter critical transonic speed range. The CAP-TSD code uses a time accurate approximate factorization algorithm for solution of the unsteady transonic small disturbance potential equation. An overview is given of the CAP-TSD code development effort along with recent algorithm modifications which are listed and discussed. Calculations are presented for several configurations including the General Dynamics 1/9th scale F-16C aircraft model to evaluate the algorithm and hence the reliability of the CAP-TSD code in general. Calculations are also presented for a flutter analysis of a 45 deg sweptback wing which agree well with the experimental data. Descriptions are presented of the CAP-TSD code and algorithm details along with results and comparisons which demonstrate the stability, accuracy, efficiency, and utility of CAP-TSD.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 2; p 467-496
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Recent advances in transonic computational aeroelasticity (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A transonic unsteady aerodynamic and aeroelasticity code called CAP-TSD was developed for application to realistic aircraft configurations. The code permits the calculation of steady and unsteady flows about complete aircraft configurations for aeroelastic analysis in the flutter critical transonic speed range. The CAP-TSD code uses a time accurate approximate factorization algorithm for solution of the unsteady transonic small disturbance potential equation. An overview is given of the CAP-TSD code development effort and results are presented which demonstrate various capabilities of the code. Calculations are presented for several configurations including the General Dynamics 1/9 scale F-16 aircraft model and the ONERA M6 wing. Calculations are also presented from a flutter analysis of a 45 deg sweptback wing which agrees well with the experimental data. Descriptions are presented of the CAP-TSD code and algorithm details along with results and comparisons which demonstrate these recent developments in transonic computational aeroelasticity.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Computers and Structures (ISSN 0045-7949); 30; 1-2,; 29-37
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Wing-flutter calculations with the CAP-TSD unsteady transonic small-disturbance program (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft (ISSN 0021-8669); 26; 876-882
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Wing flutter calculations with the CAP-TSD unsteady transonic small disturbance program (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The paper describes the application and assessment of the recently developed CAP-TSD transonic small-disturbance code for flutter predicition. The CAP-TSD program has been developed for aeroelastic analysis of complete aircraft configurations and was previously applied to the calculation of steady and unsteady pressures with favorable results. Flutter calculations are presented for two thin swept-and-tapered wing platforms with well-defined modal properties. The calculations are for Mach numbers from low subsonic to low supersonic values, including the transonic range, and are compared with subsonic linear theory and experimental flutter data. The CAP-TSD flutter results are generally in good agreement with the experimental values and are in good agreement with subsonic linear theory when wing thickness is neglected.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 88-2347 , Structures, Structural Dynamics and Materials Conference; Apr 18, 1988 - Apr 20, 1988; Williamsburg, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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