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  • 1
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    Lee-side flow phenomena on space shuttle configurations at hypersonic speeds. Part 2: Studies of lee-surface heating at hypersonic Mach numbers (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: Lee surface heating data, obtained at relatively low unit Reynolds numbers at Mach 6 and 19, are discussed with emphasis on the peak heating behavior. Surface pressures measured along the lee meridian of the delta-wing orbiter are presented and analyzed in conjunction with the heating. The effects of nose bluntness and lee surface geometry on the heating are discussed and general guidelines are presented for modifying the lee surface geometry of the shuttle to reduce vortex-induced heating. The application of the wind tunnel results to realistic shuttle flight conditions is discussed.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 451-467
    Format: text
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  • 2
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    Film cooling effectiveness in hypersonic turbulent flow (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Film cooling effectiveness in hypersonic turbulent flow from downstream surface equilibrium temperature measurement
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: ; UGREVUE(
    Format: text
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  • 3
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    Lee side heating investigations. Part 1 - Experimental lee side heating studies on a delta wing orbiter (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Lee surface flow and aerodynamic heating on delta wing orbiter
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: NASA SPACE SHUTTLE TECHNOL. CONF., VOL. 1 APR. 1971; P 267-287
    Format: text
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  • 4
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    Swept-slot film-cooling effectiveness in hypersonic turbulent flow (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Measurement results are presented for the surface equilibrium temperature downstream of swept slots, with sonic tangential air injection into a thick hypersonic turbulent boundary layer. These results are compared with unswept slot results for cooling effectiveness.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 11; May 1974
    Format: text
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  • 5
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    Effect of forward-facing jets on aerodynamic characteristics of blunt configurations at Mach 6. (1967)
    In:  Other Sources
    Details
    Publication Date: 2011-08-11
    Description: Forward facing jets effect on blunt configurations aerodynamic characteristics from wind tunnel tests at Mach 6, emphasizing drag increase
    Keywords: AERODYNAMICS
    Type: JOURNAL OF SPACECRAFT AND ROCKETS
    Format: text
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  • 6
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    Effect of compliant wall motion on turbulent boundary layers (1977)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A critical analysis of available compliant wall data which indicated drag reduction under turbulent boundary layers is presented. Detailed structural dynamic calculations suggest that the surfaces responded in a resonant, rather than a compliant, manner. Alternate explanations are given for drag reductions observed in two classes of experiments: (1) flexible pipe flows and (2) water-backed membranes in air. Analysis indicates that the wall motion for the remaining data is typified by short wavelengths in agreement with the requirements of a possible compliant wall drag reduction mechanism recently suggested by Langley.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Format: text
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  • 7
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    Multiple slot skin friction reduction (1975)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The paper investigates analytically the effect of multiple slot injection on skin friction for a representative fuselage shape (ogive-cylinder body) and evaluates the potential of slot injection as a drag reduction system in subsonic flow. Typical CTOL cruise flight conditions (Mach number equals 0.82 at altitudes of 11 km) were adopted for a fuselage 67.06 m in length and with maximum diameter of 7.32 m. The numerical method of Price and Harris (1972) was used to calculate the boundary-layer characteristics up to the first slot, while the finite-difference method of Beckwith and Bushnell (1971) was used to calculate the velocity profile downstream of one, three, five, or ten slots. An integral expression is proposed for characterizing skin friction reduction effectiveness, and it is seen that large reductions in viscous drag (50%) are available through slot injection. Skin friction reduction is improved by increasing the number of injection slots but at a diminishing rate.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 12; Sept
    Format: text
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  • 8
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    Effect of geometry modifications on effectiveness of slot injection in hypersonic flow (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The study presents wind-tunnel measurements of surface static pressures, equilibrium temperatures, and skin friction downstream of tangential slot injection into a thick turbulent hypersonic boundary layer from two modified slot configurations. The data are compared with results obtained for baseline configurations reported by Cary and Hefner (1970, 1972) to determine whether simple modifications to the slot configuration can produce improved cooling effectiveness and skin friction reduction. The baseline slot configurations are simply modified by thickening the slot lip and by elevating the location of the slot exit above the flat plate. Although the results indicate that simple modifications of the baseline slot configurations can enhance the skin friction reductions obtained with tangential slot injection, slot base drag estimates show that neither of the modifications will lessen the impact of the systems penalties for collecting, ducting, and injecting the slot air.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 14; June 197
    Format: text
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  • 9
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    Re-examination of compliant wall experiments in air with water substrates (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A possible alternative explanation is proposed for compliant wall drag reductions measured in previous investigations. Standing waves were observed to form on the surfaces of compliant wall models in air with water substrates as the freestream velocity was increased from 15 to 30 m/s. These waves resembled sine waves with half of the wave protruding over the upstream portion of the model and the other half being recessed over the downstream end of the model. These data coupled with results of recent drag reduction experiments suggest that standing waves could have caused a shift in the model center of gravity creating a bending moment that was interpreted as a reduction in the skin friction drag.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Spacecraft and Rockets; 13; Aug. 197
    Format: text
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  • 10
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    Secondary jet interaction with emphasis on outflow and jet location. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Data were obtained concerning a model which utilized a two-dimensional sonic jet. It was found that outflow and jet location significantly influence the magnitude and behavior of the secondary jet interaction forces. Continued refinements in jet interaction analyses which do not account for outflow are of limited usefulness in the design of control systems for supersonic and hypersonic vehicles. The jet total back pressure ratio increases with either jet pressure ratio or freestream Mach number.
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets; 9; Nov. 197
    Format: text
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