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  • Aircraft Design, Testing and Performance  (2)
  • 2010-2014
  • 1995-1999
  • 1950-1954  (2)
  • 1940-1944
  • 1950  (2)
  • 1
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    Experimental Investigation of Spreading Characteristics of Choked Jets Expanding into Quiescent Air (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Investigations have been conducted to determine by means of total-pressure surveys the boundaries of single and twin jets discharging through convergent nozzles into quiescent air. The jet boundaries for the region from the nozzle outlets to a station 6 nozzle diameters downstream are presented for nozzle pressure ratios ranging from 2.5 t o 16.0 and for twin-Jet nozzle center-line spacings ranging from 1.42 to 2.50 nozzle diameters. The effects of these parameters on the interaction of twin Jets are discussed. In order to ascertain the utility of the results for other than the test conditions, the effects of jet temperature, Reynolds number, and humidity on the pressure boundaries have been briefly investigated. The result indicate that for a jet of 2.6 the pressure boundaries are slightly smaller than those of corresponding unheated jets and that the effects of Reynolds number and humidity are negligible.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E50E03a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Vibration of a Wing of Finite Span in a Supersonic Flow (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An investigate ion was made of the disturbed motion of a gas for the harmonic vibrations of a thin slightly cambered wing of finite span moving forward with supersonic velocity. This problem was considered by E. A. Krasilshchikova who applied the method of Fourier series and obtained a solution of the space problem for the condition that the Mach cones drawn through the leading edge of the wing intersect the wing or are tangent to it. In this paper, a different method of solution is given, which is free from the previously mentioned condition. In particular, the vibrations of a triangular wing lying within the Mach cone are considered.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1257 , Prikladnaya Matematika i Mekhanika; 11; 371-376
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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