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  • 1
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    Near-Field and Far-Field Noise Surveys of Solid-Fuel Rocket Engines for a Range of Nozzle Exit Pressures (1959)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements of near- and far-field noise pressures are presented for a 1,500-pound-thrust engine and for several 5,000-pound-thrust engines for which the nozzle exit pressure was changed systematically in order to study its effects on the noise level and spectra. Near-field surveys indicated that the highest noise pressure occurred at about 20 exit diameters downstream if the nozzle near the transition from super-sonic to subsonic flow. The acoustical power radiated from all engines averaged about 0.5 percent of the mechanical power of the exhaust stream, the least noise being radiated by the nozzle having an exit pressure less than atmospheric. The rocket engines of these tests radiate more power per cycle at the lower frequencies than arte reported for subsonic jets in other related studies.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-TN-D-21
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The Smoke-Trail Method for Obtaining Detailed Measurements of the Vertical Wind Profile for Application to Missile-Dynamic-Response Problems (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: Detailed measurements of the vertical profile of the wind are urgently needed f o r studies of the response of rising missiles, but conventional wind-measuring systems cannot provide the accuracy and detail required over the necessary range of altitudes. A method is presented for obtaining a detailed, accurate profile over a large altitude range. The method utilizes photogrammetric measurement of successive positions of the t rail of an ascending rocket. Construction of a rocketborne smoke generator is discussed and the photography, film reading, and data-reduction procedures are described. The accuracy of the method i s examined and error equations are derived. Finally, some examples of wind profiles measured by this method are shown, and their implications for missile response are indicated.
    Keywords: Instrumentation and Photography
    Type: NASA-TN-D-976 , L-1331
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Static Investigation of Paddle Vane Oscillating in Jet of 1,300-Pound-Thrust Rocket Motor (1958)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The results of a static investigation conducted to measure the normal forces on the entire jet-vane assembly and the hinge moments on the jet vane produced by a paddle vane oscillating in the jet of a 1,500-pound-thrust rocket motor are presented for vane-deflection angles from -5 deg to 25 deg. A maximum average normal force of 71 pounds with a corresponding value for maximum average hinge moment of 228 inch-pounds was obtained with the maximum area of jet vane immersed at a jet-vane angle of 25 deg decrease in thrust caused by immersion of the jet vane varied from a maximum loss of about 58 pounds, or approximately 5 percent at maximum jet-vane angle of 25 deg, to zero loss at jet-vane angles less than approximately 10 deg.
    Keywords: Spacecraft Propulsion and Power
    Type: NASA-MEMO-10-19-58L
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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