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  • 1
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    Experimental investigation of tangential blowing for control of the strong shock boundary layer interaction on inlet ramps (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 0.165-scale isolated inlet model was tested in the NASA Lewis Research Center 8-ft by 6-ft Supersonic Wind Tunnel. Ramp boundary layer control was provided by tangential blowing from a row of holes in an aft-facing step set into the ramp surface. Testing was performed at Mach numbers from 1.36 to 1.96 using both cold and heated air in the blowing system. Stable inlet flow was achieved at all Mach numbers. Blowing hole geometry was found to be significant at 1.96M. Blowing air temperature was found to have only a small effect on system performance. High blowing levels were required at the most severe test conditions.
    Keywords: AERODYNAMICS
    Type: NASA-CR-165390 , NAS 1.26:165390 , NOR-81-127
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Aerodynamic characteristics of a vectored-thrust V/STOL fighter in the transition speed range (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind-tunnel investigation was conducted with a vectored-thrust V/STOL fighter configuration. The model was equipped with two nacelle-mounted vectored-thrust jet simulators and one lift-jet simulator. The vectored-thrust jet could be tested at two alternate longitudinal positions and three nozzle deflection angles. The vectored-thrust configuration with the rear nozzles showed an increase in lift and a decrease in pitching moment when compared with the forward nozzles. The rear nozzles also improve stall characteristics.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7191 , L-8457
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Tangential blowing for control of strong normal shock - Boundary layer interactions on inlet ramps (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The use of tangential blowing from a row of holes in an aft facing step is found to provide good control of the ramp boundary layer, normal shock interaction on a fixed geometry inlet over a wide range of inlet mass flow ratios. Ramp Mach numbers of 1.36 and 1.96 are investigated. The blowing geometry is found to have a significant effect on system performance at the highest Mach number. The use of high-temperature air in the blowing system, however, has only a slight effect on performance. The required blowing rates are significantly high for the most severe test conditions. In addition, the required blowing coefficient is found to be proportional to the normal shock pressure rise.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-1082 , Joint Propulsion Conference; Jun 21, 1982 - Jun 23, 1982; Cleveland, OH
    Format: text
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    NASA TECHNICAL REPORTS
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