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  • 1
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    Effects of roughness on heating and boundary-layer transition. Part 2: effects of discrete roughness on heating (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: A preliminary investigation on the effects of roughness on heating in delta wing orbiters was conducted on the windward surface of the vehicle. The purpose of the experiment was to determine the feasibility of using parametric relationships obtained from discrete roughness effects on heating in flat plates and cones, to complex shuttle configurations. An attempt was also made to characterize what parameters were needed to influence roughness. Experimental results show that effective roughness Reynolds numbers are less than or equal to those of flat plates at the same edge Mach number, but, the roughness correlations for plates and cones cannot be applied to the shuttle configuration.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 395-411
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A comparison of boundary-layer transition data from temperature-sensitive paint and thermocouple techniques (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Temperature sensitive paint and thermocouple techniques comparison for boundary layer transition data, considering aerodynamic heating and transition Reynolds numbers
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; YAL SOCIETY (
    Format: text
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  • 3
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    Flow fields and aerodynamic heating of space shuttle orbiters (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Wind tunnel simulations of flow fields and aerothermodynamics of space shuttle orbiters
    Keywords: FLUID MECHANICS
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 21-73
    Format: text
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  • 4
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    The effect of angle of attack on boundary-layer transition on cones. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Boundary-layer transition on 5- and 15-deg half-angle cones was studied as a function of angle of attack (ranging from 0 to 20 deg) in a 3.5 ft hypersonic wind tunnel at a freestream Mach number of 7.4. It is shown that the influence of the angle of attack on the transition Reynolds number is a function of the meridian angle. On the windward ray of the 15-deg cone, transition Reynolds numbers show an initial slight increase and then a decrease with increasing angle of attack; leeward-ray Reynolds numbers for this cone decrease rapidly with angle of attack. Windward-ray transition Reynolds numbers increase monotonically with angle of attack on the 5-deg cone, but the effect of the angle of attack on the leeward ray is the same as for the 15-deg cone.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Aug. 197
    Format: text
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  • 5
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    Calculation of metric coefficients for streamline coordinates. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A procedure is given for deriving the equations describing the surface streamline metric in a general form and in a form suitable for incorporation into computer codes to calculate an inviscid flow about three-dimensional bodies. Sample results are included to show the application of the metric in conjunction with an axisymmetric analog to predict heat transfer to a typical space shuttle orbiter.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 10; Nov. 197
    Format: text
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  • 6
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    Application of shock capturing and characteristics methods to shuttle flow fields (1972)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The calculation of real gas flows around the space shuttle vehicle can be accomplished by the method of characteristics (MOC) or shock capture technique (SCT). Results obtained with these methods for an early orbiter shape proposed by the North American Rockwell Corporation and also for the more recent 040A configuration suggested by NASA-MSC are presented. Results obtained with the SCT code demonstrate its three-dimensional, multiple shock capturing capability while results obtained with the MOC code demonstrate the calculation of equilibrium real gas flows and the determination of flow variables required for a heating analysis.
    Keywords: FLUID MECHANICS
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 1; p 65-92
    Format: application/pdf
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  • 7
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    FM telemetry for multiple force measurements on free-flying models in wind tunnels. (1966)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: Simultaneous FM telemetry measurement of four aerodynamic forces acting on free flying models in wind tunnel
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: text
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  • 8
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    A supercritical airfoil experiment (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The purpose of this investigation is to provide a comprehensive data base for the validation of numerical simulations. The objective of the present paper is to provide a tabulation of the experimental data. The data were obtained in the two-dimensional, transonic flowfield surrounding a supercritical airfoil. A variety of flows were studied in which the boundary layer at the trailing edge of the model was either attached or separated. Unsteady flows were avoided by controlling the Mach number and angle of attack. Surface pressures were measured on both the model and wind tunnel walls, and the flowfield surrounding the model was documented using a laser Doppler velocimeter (LDV). Although wall interference could not be completely eliminated, its effect was minimized by employing the following techniques. Sidewall boundary layers were reduced by aspiration, and upper and lower walls were contoured to accommodate the flow around the model and the boundary-layer growth on the tunnel walls. A data base with minimal interference from a tunnel with solid walls provides an ideal basis for evaluating the development of codes for the transonic speed range because the codes can include the wall boundary conditions more precisely than interference connections can be made to the data sets.
    Keywords: Aerodynamics
    Type: OTN-035236 , OTN-BIBL-AGARD-AR-303-Vol-2
    Format: text
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  • 9
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    Charts for equilibrium and frozen nozzle flows of carbon dioxide (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-24
    Description: Equilibrium and frozen flow property charts for carbon dioxide
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA-SP-3019
    Format: application/pdf
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  • 10
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    Contouring tunnel walls to achieve free-air flow over a transonic swept wing (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The effects of wind-tunnel walls on the flow over a swept wing were greatly reduced by wall contouring. Significant reductions in spanwise pressure gradients were achieved by shaping all of the walls to conform to the streamlines over the model in free air. Surface pressure and oil-flow data were used to evaluate the effects of Mach and Reynolds numbers on the design. Comparisons of these data with inviscid calculations indicate that free-air flow is established at a Mach number of 0.74 and at Reynolds numbers above 4.7 million.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-1725
    Format: text
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