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  • 1
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    Thin-layer and full Navier-Stokes, locally-conical and three-dimensional asymmetric solutions (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The unsteady, compressible thin-layer and full Navier-Stokes equations are used to numerically simulate steady and unsteady asymmetric, supersonic, locally-conical flows around a 5-deg-semiapex angle circular cone. The main computational scheme used for the present computations is the implicit, upwind, flux-difference splitting, finite-volume scheme. Comparisons of the solutions using the two sets of equations are presented for the flow asymmetry and its control. Computational studies are also presented to investigate the effects of the freestream Reynolds number and the locally-scaled Reynolds number on the flow asymmetry. These studies are carried out using the full Navier-Stokes equations. Three-dimensional, asymmetric flow solutions are also presented for a 5-deg-semiapex angle cone of unit length and a cone-cylinder configuration. The three-dimensional solutions are obtained by using the thin-layer equations and short-duration transient side-slip disturbances along with a very fine grid.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-0547
    Format: text
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  • 2
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    Additional experiments with flat-top wing- body combinations at high supersonic speeds (1957)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Flat top wing body configuration effects on aerodynamic characteristics of supersonic aircraft
    Keywords: AERODYNAMICS
    Type: NACA-RM-A56111
    Format: application/pdf
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  • 3
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    Comparison of uniform perturbation solutions and numerical solutions for some potential flows past slender bodies (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Approximate solutions for potential flow past an axisymmetric slender body and past a thin airfoil are calculated using a uniform perturbation method and then compared with either the exact analytical solution or the solution obtained using a purely numerical method. The perturbation method is based upon a representation of the disturbance flow as the superposition of singularities distributed entirely within the body, while the numerical (panel) method is based upon a distribution of singularities on the surface of the body. It is found that the perturbation method provides very good results for small values of the slenderness ratio and for small angles of attack. Moreover, for comparable accuracy, the perturbation method is simpler to implement, requires less computer memory, and generally uses less computation time than the panel method. In particular, the uniform perturbation method yields good resolution near the regions of the leading and trailing edges where other methods fail or require special attention.
    Keywords: AERODYNAMICS
    Type: NASA-CR-172485 , ICASE-84-56 , NAS 1.26:172485
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  • 4
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    Implementation of uniform perturbation method for potential flow past axisymmetric and two-dimensional bodies (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-20
    Description: The aerodynamic characteristics of potential flow past an axisymmetric slender body and a thin airfoil are calculated using a uniform perturbation analysis method. The method is based on the superposition of potentials of point singularities distributed inside the body. The strength distribution satisfies a linear integral equation by enforcing the flow tangency condition on the surface of the body. The complete uniform asymptotic expansion of its solution is obtained with respect to the slenderness ratio by modifying and adapting an existing technique. Results calculated by the perturbation analysis method are compared with the existing surface singularity panel method and some available analytical solutions for a number of cases under identical conditions. From these comparisons, it is found that the perturbation analysis method can provide quite accurate results for bodies with small slenderness ratio. The present method is much simpler and requires less memory and computation time than existing surface singularity panel methods of comparable accuracy.
    Keywords: AERODYNAMICS
    Type: NASA-CR-173829 , NAS 1.26:173829
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  • 5
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    Separation-bubble flow solution using Euler/Navier-Stokes zonal approach with downstream compatibility conditions (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: The two-dimensional flow over a blunt leading-edge plate is simulated on the basis of an Euler/Navier-Stokes zonal scheme. The scheme uses an implicit upwind finite-volume scheme, which is based on the van Leer flux-vector splitting. It is shown that the Euler/Navier-Stokes zonal scheme with downstream boundary-layer compatibility conditions is accurate and efficient.
    Keywords: AERODYNAMICS
    Type: Journal of Scientific Computing (ISSN 0885-7474); 3; 121-137
    Format: text
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  • 6
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    Adaptation of muscle gene expression to changes in contractile activity (1987)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A review of the existing literature regarding the effects of different types of physical activities on the gene expression of adult skeletal muscles leads us to conclude that each type of exercise training program has, as a result, a different phenotype, which means that there are multiple mechanisms, each producing a unique phenotype. A portion of the facts which support this position is presented and interpreted here. [Abstract translated from the original French by NASA].
    Keywords: Aerospace Medicine
    Type: Advances in myochemistry (ISSN 0952-1410); 1; 205-16
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  • 7
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    Numerical simulation of steady and unsteady asymmetric vortical flow (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The unsteady, compressible, thin-layer, Navier-Stokes equations are solved to simulate steady and unsteady, asymmetric, vortical laminar flow around cones at high incidences and supersonic Mach numbers. The equations are solved by using an implicit, upwind, flux-difference splitting, finite-volume scheme. Locally conical flows are assumed and the solutions are obtained by forcing the conserved components of the flowfield vector to be equal at two axial stations located at 0.95 and 1.0. Computational examples cover steady and unsteady asymmetric flows around a circular cone and its control using side strakes. Unsteady asymmetric flows are also presented for elliptic- and diamond-section cones, which model asymmetric vortex shedding around round and sharp-edged delta wing flows.
    Keywords: AERODYNAMICS
    Type: International Symposium on Nonsteady Fluid Dynamics; Jun 04, 1990 - Jun 07, 1990; Toronto; Canada
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  • 8
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    Comparison of uniform perturbation and numerical solutions for some potential flows past slender bodies (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Approximate solutions for potential flow past an axisymmetric slender body and past a thin airfoil are calculated using a uniform perturbation method and then compared with either the exact analytical solution or the solution obtained using a purely numerical method. The perturbation method is based upon a representation of the disturbance flow as the superposition of singularities distributed entirely within the body, while the numerical (panel) method is based upon a distribution of singularities on the surface of the body. It is found that the perturbation method provides very good results for small values of the slenderness ratio and for small angles of attack. Moreover, for comparable accuracy, the perturbation method is simpler to implement, requires less computer memory, and generally uses less computation time than the panel method. In particular, the uniform perturbation method yields good resolution near the regions of the leading and trailing edges where other methods fail or require special attention.
    Keywords: AERODYNAMICS
    Type: Computers and Fluids (ISSN 0045-7930); 13; 3 19; 271-283
    Format: text
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