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  • PROPULSION SYSTEMS  (118)
  • FLUID MECHANICS  (90)
  • ASTROPHYSICS
  • 1970-1974  (208)
  • 1972  (89)
  • 1971  (119)
Collection
Keywords
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  • 1970-1974  (208)
Year
  • 1
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    V/STOL propulsion (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Propulsion technology for STOL and V/STOL commercial aircraft
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 135-168
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    A study of nozzle and ejector flow problems by the method of integral relations (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The application of the method of integral relations to nozzle and ejector flow problems was examined. For nozzle flow problems, the general formulation is that the approaching flow may be rotational. Particular attention was given to the phenomenon of choking under nonuniform flow conditions. Numerical integration of the governing ordinary differential equations was also investigated. This scheme of analysis was also applied to study the interacting flow field within an ejector system.
    Keywords: FLUID MECHANICS
    Type: NASA-CR-128066 , UILU-ENG-72-4002 , ME-TR-395-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Numerical solutions of several reflected shock-wave flow fields with nonequilibrium chemical reactions (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The method of characteristics for a chemically reacting gas is used in the construction of the time-dependent, one-dimensional flow field resulting from the normal reflection of an incident shock wave at the end wall of a shock tube. Nonequilibrium chemical reactions are allowed behind both the incident and reflected shock waves. All the solutions are evaluated for oxygen, but the results are generally representative of any inviscid, nonconducting, and nonradiating diatomic gas. The solutions clearly show that: (1) both the incident- and reflected-shock chemical relaxation times are important in governing the time to attain steady state thermodynamic properties; and (2) adjacent to the end wall, an excess-entropy layer develops wherein the steady state values of all the thermodynamic variables except pressure differ significantly from their corresponding Rankine-Hugoniot equilibrium values.
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-6885 , A-4226
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Upper-stage space shuttle propulsion by means of separate scramjet and rocket engines (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A preliminary mission study of a reusable vehicle from staging to orbit indicates payload advantages for a dual-propulsion system consisting of separate scramjet and rocket engines. In the analysis the scramjet operated continuously and the initiation of rocket operation was varied. For a stage weight of 500,000 lb the payload was 10.4 percent of stage weight or 70 percent greater than that of a comparable all-rocket-powered stage. When compared with a reusable two-state rocket vehicle having 50,000 lb payload, the use of the dual propulsion system for the second stage resulted in significant decreases in lift-off weight and empty weight, indicating possible lower hardware costs.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-6762 , E-6555
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A study of internal drag of small-scale ducts at Mach number 4 (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental investigation was made to examine the applicability of methods used to determine internal drag of small ducts and to study some of the problems encountered in assessing momentum losses in such ducts. Test Mach numbers ranged from 3.7 to 4.4 at angles of attack of 0 and 5 degrees and at a constant Reynolds number of 4.3 million per foot. The configurations represented small ducts used to simulate external aerodynamics of air breathing propulsion systems and consisted of wing nacelle models of ducts with circular, square, and rectangular inlets and with a two-dimensional inlet.
    Keywords: FLUID MECHANICS
    Type: NASA-TM-X-62143
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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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
  • 7
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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
  • 8
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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
  • 9
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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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  • 10
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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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