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  • 1
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    Supersonic Flow past a Family of Blunt Axisymmetric Bodies (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Some 100 numerical computations have been carried out for unyawed bodies of revolution with detached bow waves. The gas is assumed perfect with gamma = 5/3, 7/5, or 1. Free-stream Mach numbers are taken as 1.2, 1.5, 2, 3, 4, 6, 10, and infinity. The results are summarized with emphasis on the sphere and paraboloid.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TR-R-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Effect of External Boundary Layer on Performance of Axisymmetric Inlet at Mach Numbers of 3.0 and 2.5 (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: The effect of an external boundary layer on the performance of an axisymmetric external-internal-compression inlet was evaluated at Mach numbers of 3.0 and 2.5 and Reynolds numbers from 2.2 to 0.5 x 10(exp 6) per foot. The inlet was tested at locations up to two-thirds of the way into the 1.7- and 9.0-inch boundary layers generated by a flat plate and the tunnel floor, respectively. The inlet could be readily started at all conditions tested, including those where the boundary layer was separated upstream of the inlet by the various shock systems during the restart cycle. Although the inlet performance decreased with increasing immersion into the boundary layer at both Mach numbers, the inlet was more sensitive to boundary-layer ingestion at the design Mach number of 3.0.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TM-X-49
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Second-Order Slender-Body Theory-Axisymmetric Flow (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Slender-body theory for subsonic and supersonic flow past bodies of revolution is extended to a second approximation, Methods are developed for handling the difficulties that arise at round ends, Comparison is made with experiment and with other theories for several simple shapes.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TR-R-47
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Effects of Yaw on the Heat Transfer to a Blunt Cone-Cylinder Configuration at a Mach Number of 1.98 (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: A heat-transfer investigation has been made on a blunt cone-cylinder model at a Mach number of 1.98 at yaw angles from 0 deg to 9 deg. The results indicate that, except for the hemispherical nose, the heat-transfer coefficient increased on the windward side and decreased on the leeward side as yaw angle was increased. In general, the increase in heat transfer on the windward side was higher than the corresponding decrease on the leeward side. A comparison with theory (NACA Technical Note 4208) yielded agreement which was, in general, within 10 percent on the cone at all test conditions and on the cylinder at an angle of yaw of 0 deg.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-MEMO-10-8-58L
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Estimated Performance of Radial-Flow Exit Nozzles for Air in Chemical Equilibrium (1959)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The thrust, boundary-layer, and heat-transfer characteristics were computed for nozzles having radial flow in the divergent part. The working medium was air in chemical equilibrium, and the boundary layer was assumed to be all turbulent. Stagnation pressure was varied from 1 to 32 atmospheres, stagnation temperature from 1000 to 6000 R, and wall temperature from 1000 to 3000 R. Design pressure ratio was varied from 5 to 320, and operating pressure ratio was varied from 0.25 to 8 times the design pressure ratio. Results were generalized independent of divergence angle and were also generalized independent of stagnation pressure in the temperature range of 1000 to 3000 R. A means of determining the aerodynamically optimum wall angle is provided.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-MEMO-1-5-59E , E-125
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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