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  • 1
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    Calculative techniques for transonic flows (1970)
    In:  CASI
    Details
    Publication Date: 2005-11-27
    Description: Calculation methods for predicting transonic aerodynamic characteristics of wing-body combinations
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON ANAL. METHODS IN AIRCRAFT AERODYN. 1970; P 53-73
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  • 2
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    Approximate analytic solution for the position and strength of shock waves about cones in supersonic flow (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Approximate solution for position and strength of shock waves about cones in steady supersonic flow
    Keywords: AERODYNAMICS
    Type: ; ADEMIE DES SCIENCES
    Format: text
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  • 3
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    Thin-layer approximation for three-dimensional supersonic corner flows (1980)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The thin-layer approximation is extended to an axial corner that is formed by the intersection of two perpendicular plates, one of which has an inclination angle with respect to the free stream. A computer code developed by Hung and MacCormack (1978) is modified for the thin-layer approximation, and a case with Mach 5.9 and a wedge angle of 6 deg is computed. In addition, it is shown that it is not necessary to solve the complete Navier-Stokes equations for a three-dimensional high-Reynolds-number corner flow.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 18; Dec. 198
    Format: text
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  • 4
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    Separation bubble behavior for a NACA 23009 airfoil (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Results are reported of experiments with smoke-wire flow visualization applied to characterizing the conditions conducive to formation of a separation bubble on an airfoil in low Re flow. An airfoil was used which spanned the test channel of the wind tunnel designed for low turbulence and noise. A wire coated with mineral oil was stretched across the channel upstream of the airfoil and heated. The smoke it gave off was flash-illuminated and photographed with ASA 3000 film. Extending the airfoil over the entire section yielded photographs that gave an essentially two-dimensional perspective. Angles of attack from 0-10 deg were investigated at Re of 33,000, 66,000, 100,000 and 133,000. Sample photographs illustrate the usefulness of the technique and apparatus in the flow regimes examined, particularly when used in conjunction with pressure tap data from the airfoil surface.
    Keywords: AERODYNAMICS
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  • 5
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    Numerical studies of unsteady transonic flow over oscillating airfoil (1985)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A finite difference solution to the Navier-Stokes equations combined with a time varying grid generation technique was used to compute unsteady transonic flow over an oscillating airfoil. These computations were compared with experimental data (obtained at Ames Research Center) which form part of the AGARD standard configuration for aeroelastic analysis. A variety of approximations to the full Navier-Stokes equations was used to determine the effect of frequency, shock wave motion, flow separation, and airfoil geometry on unsteady pressures and overall air loads. Good agreement is shown between experiment and theory with the limiting factor being the lack of a reliable turbulence model for high Reynolds number, unsteady transonic flows.
    Keywords: AERODYNAMICS
    Type: AGARD Transonic Unsteady Aerodyn. and its Aeroelastic Appl.; 22 p
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  • 6
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    Experimental studies of scale effects on oscillating airfoils at transonic speeds (1981)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Scale effects are discussed with reference to a conventional airfoil (NACA 64A010) and a supercritical airfoil (NLR 7301) at mean flow conditions that support both weak and strong shock waves. During the experiment the Reynolds number was varied from 3 x 10 to the sixth power at time history data are presented over the range of reduced frequencies that are important in aeroelastic applications. The experimental data show that viscous effects are important in the case of the supercritical airfoil at all flow conditions and in the case of the conventional airfoil under strong shock wave conditions. Some frequency dependent viscous effects were also observed.
    Keywords: AERODYNAMICS
    Type: AGARD Boundary Layer Effects on Unsteady Airfoils; 13 p
    Format: text
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  • 7
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    Transonic cascade flow prediction using the Navier-Stokes equations (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents results which summarize the work carried out during the last three years to improve the efficiency and accuracy of numerical predictions in turbomachinery flow calculations. A new kind of nonperiodic c-type grid is presented and a Runge-Kutta scheme with accelerating strategies is used as a flow solver. The code capability is presented by testing four different blades at different exit Mach numbers in transonic regimes. Comparison with experiments shows the very good reliability of the numerical prediction. In particular, the loss coefficient seems to be correctly predicted by using the well-known Baldwin-Lomax turbulence model.
    Keywords: AERODYNAMICS
    Type: ASME PAPER 91-GT-313
    Format: text
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  • 8
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    The critical role of computational fluid dynamics in rotary-wing aerodynamics (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The field of helicopter rotor aerodynamics is basically the study of unsteady aerodynamic flows in a rotating and translating coordinate system. Current trends in this field are briefly reviewed by examining recent advances in lifting-surface theory, wake modeling, panel methods, and finite-difference models. Examples are used to illustrate selected current methods and some indications of promising future directions are highlighted.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0336
    Format: text
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  • 9
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    Flow prediction for propfan engine installation effects on transport aircraft at transonic speeds (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An Euler-based method for aerodynamic analysis of turboprop transport aircraft at transonic speeds has been developed. In this method, inviscid Euler equations are solved over surface-fitted grids constructed about aircraft configurations. Propeller effects are simulated by specifying sources of momentum and energy on an actuator disc located in place of the propeller. A stripwise boundary layer procedure is included to account for the viscous effects. A preliminary version of an approach to embed the exhaust plume within the global Euler solution has also been developed for more accurate treatment of the exhaust flow. The resulting system of programs is capable of handling wing-body-nacelle-propeller configurations. The propeller disks may be tractors or pushers and may represent single or counterrotation propellers. Results from analyses of three test cases of interest (a wing alone, a wing-body-nacelle model, and a wing-nacelle-endplate model) are presented. A user's manual for executing the system of computer programs with formats of various input files, sample job decks, and sample input files is provided in appendices.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3954 , NAS 1.26:3954
    Format: application/pdf
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  • 10
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    Flight research on natural laminar flow nacelles - A progress report (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents a progress report on an ongoing flight experiment for natural laminar flow nacelles. The results given herein were obtained during the first phase of the experiment, in which an instrumented natural laminar flow nacelle fairing was flight tested in the presence of turbofan engine noise and a controlled noise source. The results indicate that with the controlled noise source off, natural laminar flow was measured as far aft as 37 percent of the fairing length. The transition front was irregular in contour, and the extent of natural laminar flow was significantly affected by the relative flow angle for the fairing. In addition to these test results, the paper discusses the results of some recent computational analyses to predict pressure distributions and transition location, and to explain some of the data trends. Comparisons between measured and predicted data indicate that the analytical methods successfully predicted trends for the baseline (no controlled noise source) studies.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-1629
    Format: text
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