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  • PROPULSION SYSTEMS  (170)
  • ASTROPHYSICS
  • FLUID MECHANICS
  • 1970-1974  (292)
  • 1973  (84)
  • 1972  (89)
  • 1971  (119)
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Keywords
Years
  • 1970-1974  (292)
Year
  • 1973  (84)
  • 1972  (89)
  • 1971  (119)
  • 1974  (105)
  • 1970  (107)
  • 11
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    Jet-noise reduction through liquid-base foam injection. (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation has been made of the sound-absorbing properties of liquid-base foams and of their ability to reduce jet noise. Protein, detergent, and polymer foaming agents were used in water solutions. A method of foam generation was developed to permit systematic variation of the foam density. The investigation included measurements of sound-absorption coefficents for both plane normal incidence waves and diffuse sound fields. The intrinsic acoustic properties of foam, e.g., the characteristic impedance and the propagation constant, were also determined. The sound emitted by a 1-in.-diam cold nitrogen jet was measured for subsonic (300 m/sec) and supersonic (422 m/sec) jets, with and without foam injection. Noise reductions up to 10 PNdB were measured.
    Keywords: PROPULSION SYSTEMS
    Type: Acoustical Society of America; vol. 50
    Format: text
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    NASA TECHNICAL REPORTS
  • 12
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    An implicit finite-difference solution to the viscous shock layer, including the effects of radiation and strong blowing (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An implicit finite-difference scheme is developed for the fully coupled solution of the viscous, radiating stagnation-streamline equations, including strong blowing. Solutions are presented for both air injection and injection of carbon-phenolic ablation products into air at conditions near the peak radiative heating point in an earth entry trajectory from interplanetary return missions. A detailed radiative-transport code that accounts for the important radiative exchange processes for gaseous mixtures in local thermodynamic and chemical equilibrium is utilized in the study. With minimum number of assumptions for the initially unknown parameters and profile distributions, convergent solutions to the full stagnation-line equations are rapidly obtained by a method of successive approximations. Damping of selected profiles is required to aid convergence of the solutions for massive blowing. It is shown that certain finite-difference approximations to the governing differential equations stabilize and improve the solutions. Detailed comparisons are made with the numerical results of previous investigations. Results of the present study indicate lower radiative heat fluxes at the wall for carbonphenolic ablation than previously predicted.
    Keywords: FLUID MECHANICS
    Type: NASA-TR-R-388 , L-8302
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 13
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    Analysis of cavitation bubble dynamics in a liquid (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: General differential equations governing the dynamics of the cavitation bubbles in a liquid were derived. With the assumption of spherical symmetry the governing equations were simplified. Closed form solutions were obtained for simple cases, and numerical solutions were calculated for complicated ones. The growth and the collapse of the bubble were analyzed, oscillations of the bubbles were studied, and the stability of the cavitation bubbles were investigated. The results show that the cavitation bubbles are unstable, and the oscillation is not sinusoidal.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-121057 , UR-00013
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 14
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    A study of the use of liquid base foams for jet noise reduction (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Acoustical properties of liquid base foams and application for jet noise reduction
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-1695
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 15
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    Auxiliary power unit design studies. Space shuttle APU system selection and performance (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Space shuttle auxiliary power unit design selection and performance evaluation
    Keywords: PROPULSION SYSTEMS
    Type: NASA. MARSHALL SPACE FLIGHT CENTER PROC.- SPACE TRANSPORTATION SYSTEM PROPULSION TECHNOL. CONF., VOL. 3 28 APR. 1971; P 1099-1122
    Format: text
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    NASA TECHNICAL REPORTS
  • 16
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    Compressible flow across shaft face seals (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Analysis of compressible flow across shaft face seals
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-52959
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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    Laser Doppler velocimeter investigation of trailing vortices behind a semi-span swept wing in a landing configuration (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Measured axial and tangential velocity profiles in the near wake vortices of a semi-span model of the Convair 990 wing in the NASA-Ames 7- by 10-foot wind tunnel are presented. A scanning laser Doppler velocimeter was used to obtain data at two different downstream stations (0.49 and 1.25 wing spans) at various angles of attack and configurations from wing alone to wing plus nacelles, anti-shock bodies, and flaps deflected 27 deg (landing configuration). It is shown that the velocity distributions within the wake are quite sensitive to span loading. Specifically, it is illustrated that an aircraft flying at given lift coefficient (C SUB L), can substantially reduce its trailing vortex upset potential by deploying its flaps and altering its flight attitude to maintain the same C SUB L. This might be taken into consideration along with performance and noise considerations in the selection of aircraft approach lift over drag.
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-62294
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 18
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    Solid propellant rocket motor (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The characteristics of a solid propellant rocket engine with a controlled rate of thrust buildup to a desired thrust level are discussed. The engine uses a regressive burning controlled flow solid propellant igniter and a progressive burning main solid propellant charge. The igniter is capable of operating in a vacuum and sustains the burning of the propellant below its normal combustion limit until the burning propellant surface and combustion chamber pressure have increased sufficiently to provide a stable chamber pressure.
    Keywords: PROPULSION SYSTEMS
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    Non-steady flow direction generation and measurement (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flow direction generator for testing sensitivity of flowmeter to unsteady pressure
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-52962
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 20
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    Highly noise suppressed bypass 6 engine for STOL application (1973)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A TF-34 engine with an acoustically treated ground test nacelle was built and tested to determine the feasibility of suppressing fan and core engine noise to the stringent levels required for STOL or short-haul commercial aircraft. The design incorporates wall treatment for the fan and core plus three treated splitter rings in the inlet and two treated splitters in the aft fan duct. Maximum suppression of fan tone noise of 40-45 dB was obtained from both the inlet and aft fan treatment. At rated fan speed, overall noise was reduced by 21 PNdB to a value of 94 PNdB on a 500-foot sideline. The overall noise reduction value was limited by the jet noise floor. Thrust losses due to the acoustic treatment are also discussed.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 73-1031 , Aero-Acoustics Conference; Oct 15, 1973 - Oct 17, 1973; Seattle, WA
    Format: text
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    NASA TECHNICAL REPORTS
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