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  • 1
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    On the numerical solution of two-dimensional, laminar compressible flows with imbedded shock waves. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The complete, time-dependent Navier-Stokes equations are expressed in conservation form and solved by employing an explicit finite difference numerical technique which incorporates artificial viscosity terms of the form first suggested by Rusanov for numerical stability in the vicinity of shock waves. Surface boundary conditions are developed in a consistent and unique manner through the use of a physically oriented extrapolation procedure. From numerical experimentation an extended range for the explicit stability parameter is established. Also employed is an additional convergence parameter which relates incremental spatial steps. Convergence of the transient solution to a steady state flow was obtained after 400 to 500 time steps.
    Keywords: FLUID MECHANICS
    Type: ASME PAPER 72-FE-7
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Analysis of a two-dimensional type 6 shock-interference pattern using a perfect-gas code and a real-gas code (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Numerical codes were developed to calculate the two dimensional flow field which results when supersonic flow encounters double wedge configurations whose angles are such that a type 4 pattern occurs. The flow field model included the shock interaction phenomena for a delta wing orbiter. Two numerical codes were developed, one which used the perfect gas relations and a second which incorporated a Mollier table to define equilibrium air properties. The two codes were used to generate theoretical surface pressure and heat transfer distributions for velocities from 3,821 feet per second to an entry condition of 25,000 feet per second.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-134010 , REPT-73003
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Hypersonic shock-interaction phenomena applicable to space shuttle configurations (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The convective heat transfer distribution for space shuttle configurations is discussed. The viscous/inviscid interactions associated with the complex three dimensional flow fields are examined. Two basic conditions are considered as follows: (1) models consisting of basic elemental combinations and (2) models of specific flight vehicles. The test facilities and test programs used to obtain data on the fuselage flow field and the wing flow field are described.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-128586 , ER-72003
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Flow field measurements for cylindrical configurations in a hypersonic wind tunnel: Windward and leeward flow fields (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Windward and leeward measurements were made for a variety of simulated infinite cylinders exposed to hypersonic streams over an angle of attack from 30 deg to 90 deg. For the range of conditions included in the study, the following conclusions are made: (1) Swept cylinder theory provides a reasonable correlation of the measured laminar heat transfer rates from the plane of symmetry. (2) The boundary layer transition criteria in the plane of symmetry are a function of the transverse curvature. (3) Relaminarization of the circumferential boundary layer for a right circular cylinder was observed at the highest Reynolds number tested. (4) The effect of leeside geometry on the average heat transfer rate can be correlated with a single geometric parameter which is dependent on the location of separation. (5) The relationship of leeward heating to angle of attack is virtually linear for each cross section. (6) No systematic effect of free stream Reynolds number was observed.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-115467 , REPT-71007
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    An experimental investigation of the flow field for double-wedge configurations in a Mach 4.97 stream (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The viscous-inviscid interactions which perturb the flow around the wing leading edge are discussed. The flow field perturbation results when the fuselage-generated shock wave interacts with the wing-generated shock wave. Three types of shock interference patterns are possible for the wing leading edge of the orbiter.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-134386 , REPT-74003
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Analysis of test times and boundary layer induced property variations in a circular shock tube (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Test times and boundary layer induced property variations in circular shock tube
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-3759
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    A study of boundary layer transition on outgassing cones in hypersonic flow (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Surface heat-transfer rates and pressures were measured at hypersonic speeds on sharp cones at zero angle of attack with and without gas injection. Using the non-injection results for reference data the effects on heating and transition location of surface roughness and injectant rate, distribution and composition were determined. The transition location was sensitive to the injectant distribution. The transition Reynolds numbers were significantly greater when the injectant distribution was constant than with a variable distribution. The measured heat-transfer distribution were also strongly dependent upon the injectant distribution. Transition Reynolds number results obtained during this program with a variable injectant distribution were correlated with a limited amount of data available for a degrading model tested in a different facility. Transitional data with constant injectant distribution were correlated with earlier results. An empirical correlation of heat-transfer reduction due to gas injection in turbulent flow was developed for both distributions tested. Several effects of mass addition on heating and transition, which have been earlier reported, were observed.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-1908
    Format: application/pdf
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