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  • 1
    Electronic Resource
    Electronic Resource
    The application of inverse boundary layer methods to the three-dimensional viscous design problem (1986)
    New York, NY [u.a.] : Wiley-Blackwell
    Communications in Applied Numerical Methods 2 (1986), S. 57-61 
    Details
    ISSN: 0748-8025
    Keywords: Engineering ; Engineering General
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Mathematics , Technology
    Notes: The problem of designing three-dimensional configurations with specified skin friction is addressed. For wall flows that are boundary layers, the following procedure is described. The input skin friction is used as a target for an inverse boundary layer calculation. The resulting pressure distribution is used as input to an inviscid configuration design procedure. This procedure computes the body geometry. The procedure is demonstrated by modifying the lift of a wing section, in compressible flow.
    Additional Material: 4 Ill.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1002/cnm.1630020109
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Airfoil design method using the Navier-Stokes equations (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An airfoil design procedure is described that was incorporated into an existing 2-D Navier-Stokes airfoil analysis method. The resulting design method, an iterative procedure based on a residual-correction algorithm, permits the automated design of airfoil sections with prescribed surface pressure distributions. The inverse design method and the technique used to specify target pressure distributions are described. It presents several example problems to demonstrate application of the design procedure. It shows that this inverse design method develops useful airfoil configurations with a reasonable expenditure of computer resources.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft (ISSN 0021-8669); 28; 216-224
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Inverse airfoil design procedure using a multigrid Navier-Stokes method (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Modified Garabedian McFadden (MGM) design procedure was incorporated into an existing 2-D multigrid Navier-Stokes airfoil analysis method. The resulting design method is an iterative procedure based on a residual correction algorithm and permits the automated design of airfoil sections with prescribed surface pressure distributions. The new design method, Multigrid Modified Garabedian McFadden (MG-MGM), is demonstrated for several different transonic pressure distributions obtained from both symmetric and cambered airfoil shapes. The airfoil profiles generated with the MG-MGM code are compared to the original configurations to assess the capabilities of the inverse design method.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Pennsylvania State Univ., Third International Conference on Inverse Design Concepts and Optimization in Engineering Sciences (ICIDES-3); p 55-66
    Format: application/pdf
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  • 4
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    Numerical solution of unsteady rotational flow past fixed and rotary wing configurations (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The application of unsteady 3-D Euler and Navier-Stokes equations to transonic flow past rotor blades, and wing-alone configurations is described. A promising approach for the numerical solution of these equations is examined. Additional work is needed for improving the efficiency of the present procedure. It is hoped that the techniques presented will find use in fixed and rotary wing aircraft analysis.
    Keywords: AERODYNAMICS
    Type: NASA, Langley Research Center, Transonic Unsteady Aerodynamics and Aeroelasticity 1987, Part 2; p 351-374
    Format: application/pdf
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  • 5
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    Two-dimensional dynamic stall as simulated in a varying freestream (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A low speed wind tunnel equipped with a axial gust generator to simulate the aerodynamic environment of a helicopter rotor was used to study the dynamic stall of a pitching blade in an effort to ascertain to what extent harmonic velocity perturbations in the freestream affect dynamic stall. The aerodynamic moment on a two dimensional, pitching blade model in both constant and pulsating airstream was measured. An operational analog computer was used to perform on-line data reduction and plots of moment versus angle of attack and work done by the moment were obtained. The data taken in the varying freestream were then compared to constant freestream data and to the results of two analytical methods. These comparisons show that the velocity perturbations have a significant effect on the pitching moment which can not be consistently predicted by the analytical methods, but had no drastic effect on the blade stability.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-CR-164829
    Format: application/pdf
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  • 6
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    The Design of Future Airbreathing Engine Systems within an Intelligent Synthesis Environment (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes a new Initiative proposed by the National Aeronautics and Space Administration (NASA). The purpose of this initiative is to develop a future design environment for engineering and science mission synthesis for use by NASA scientists and engineers. This new initiative is called the Intelligent Synthesis Environment (ISE). The paper describes the mission of NASA, future aerospace system characteristics, the current engineering design process, the ISE concept, and concludes with a description of possible ISE applications for the decision of air-breathing propulsion systems.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-1999-209192 , NAS 1.15:209192 , E-11706 , 14th International on Air Breathing Engines; Sep 05, 1999 - Sep 10, 1999; Florence; Italy
    Format: application/pdf
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  • 7
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    Application of a new Navier-Stokes inverse method to the design of advanced airfoils (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new inverse airfoil design method has been developed. This method couples a two-dimensional Navier-Stokes code to a residual-correction design algorithm to produce an efficient design code. Since this method can be used to design airfoils near the limits of performance capabilities, a technique to investigate the limits of lift has been developed to guide the design of new airfoils. Examples of the use of the inverse Navier-Stokes code and the maximum lift technology in the design of new airfoils are presented.
    Keywords: AERODYNAMICS
    Type: AHS, Annual Forum; May 21, 1990 - May 23, 1990; Washington, DC; United States
    Format: text
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  • 8
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    An airfoil design method for viscous flows (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An airfoil design procedure is described that has been incorporated into an existing two-dimensional Navier-Stokes airfoil analysis method. The resulting design method, an iterative procedure based on a residual-correction algorithm, permits the automated design of airfoil sections with prescribed surface pressure distributions. This paper describes the inverse design method and the technique used to specify target pressure distributions. An example airfoil design problem is described to demonstrate application of the inverse design procedure. It shows that this inverse design method develops useful airfoil configurations with a reasonable expenditure of computer resources.
    Keywords: AERODYNAMICS
    Type: Southeastern Conference on Theoretical and Applied Mechanics; Mar 22, 1990 - Mar 23, 1990; Atlanta, GA; United States
    Format: text
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  • 9
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    Current status of computational methods for transonic unsteady aerodynamics and aeroelastic applications (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The current status of computational methods for unsteady aerodynamics and aeroelasticity is reviewed. The key features of challenging aeroelastic applications are discussed in terms of the flowfield state: low-angle high speed flows and high-angle vortex-dominated flows. The critical role played by viscous effects in determining aeroelastic stability for conditions of incipient flow separation is stressed. The need for a variety of flow modeling tools, from linear formulations to implementations of the Navier-Stokes equations, is emphasized. Estimates of computer run times for flutter calculations using several computational methods are given. Application of these methods for unsteady aerodynamic and transonic flutter calculations for airfoils, wings, and configurations are summarized. Finally, recommendations are made concerning future research directions.
    Keywords: AERODYNAMICS
    Type: Computing Systems in Engineering (ISSN 0956-0521); 3; 5; p. 545-569.
    Format: text
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  • 10
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    The effect of varying freestream velocity on dynamic stall characteristics (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A low speed wind tunnel equipped with an axial gust generator to simulate the aerodynamic environment of a helicopter rotor was used to study the dynamic stall of a pitching blade. The objective of this investigation was to find out to what extent harmonic velocity perturbations in the freestream affect dynamic stall. The study involved making measurements of the aerodynamic moment on a two-dimensional, pitching blade model in both constant and pulsating airstreams. Using an operational analog computer to perform on-line data reduction, plots of moment versus angle of attack and work done by the moment were obtained. The data taken in the varying freestream were then compared to constant freestream data, and to the results of two analytical methods. These comparisons showed that the velocity perturbations had a significant effect on the pitching moment which could not be consistently predicted by the analytical methods, but had no drastic effect on the blade stability.
    Keywords: AERODYNAMICS
    Type: Annual National Forum of the American Helicopter Society; May 10, 1976 - May 12, 1976; Washington, DC
    Format: text
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