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  • Aerodynamics  (1)
  • Fluid Mechanics and Thermodynamics  (1)
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  • 1
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    Unknown
    Damping in a Roll of a Missile Configuration with a Modified Triangular Wing and a Cruciform Tail at a Mach Number of 1.52 (1951)
    In:  CASI
    Details
    Publication Date: 2019-08-14
    Description: The damping-in-Toll stability derivatives of a missile configuration and its components were determined both experimentally and theoretically. The tests were conducted at a Mach number of 1.52 and at a Reynolds number, based on the mean aerodynamic chord of the wing, of 0.82 x 10(exp 6). The experimental damping derivative of the wing-body combination was 67 percent of the theoretical value. The difference is believed to have resulted mainly from the fact that the theory is not strictly applicable when the Mach number normal to the leading edge is almost unity, which was the case in the present investigation. For the tail-body combination the damping derivative was 86 percent of the theoretical value. In this case, the difference is believed to have been caused partially by mutual interference between the tail surfaces and partially by the low Reynolds number of the flow over the tail. It was found that the damping of the complete configuration was not equal to the sum of the damping derivatives of the components because of the effect of the wing downwash on the damping of the tail.
    Keywords: Aerodynamics
    Type: NACA-RM-A51A03
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Investigation of an Axisymmetric Internal Compression Inlet at a Mach Number of About 3.8 (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: An idealized axisymmetric, all-internal compression inlet was designed for a Mach number of 3.75. The objective of the design was to obtain a steady, one-dimensional transonic flow and a high over-all total pressure recovery. Boundary-layer removal was employed in the vicinity of the inflection point of the supersonic contour. Static and total-pressure fluctuations were measured in the transonic flow region. A total pressure recovery of about 90 percent was obtained with a boundary-layer-removal mass flow rate of 15 percent of the inlet mass flow rate. The accompanying root-mean-square total pressure fluctuation in the throat region was only 1 percent of the free stream total pressure. The test Mach number was 3.80 and the Reynolds number based on inlet diameter was 2.63 x 10(exp 6).
    Keywords: Fluid Mechanics and Thermodynamics
    Type: NASA-TN-D-854 , A-405
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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