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  • Biochemistry and Biotechnology  (1,127)
  • AERODYNAMICS  (571)
  • 1995-1999  (672)
  • 1985-1989  (1,026)
  • 1996  (672)
  • 1985  (1,026)
Collection
Keywords
Publisher
Years
  • 1995-1999  (672)
  • 1985-1989  (1,026)
Year
  • 1
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    NASA's hypersonic fluid and thermal physics program (Aerothermodynamics) (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: This survey paper gives an overview of NASA's hypersonic fluid and thermal physics program (recently renamed aerothermodynamics). The purpose is to present the elements of, example results from, and rationale and projection for this program. The program is based on improving the fundamental understanding of aerodynamic and aerothermodynamic flow phenomena over hypersonic vehicles in the continuum, transitional, and rarefied flow regimes. Vehicle design capabilities, computational fluid dynamics, computational chemistry, turbulence modeling, aerothermal loads, orbiter flight data analysis, orbiter experiments, laser photodiagnostics, and facilities are discussed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0922
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Deceleration of a supersonic flow behind a curved shock wave with isentropic precompression (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Three-dimensional supersonic flows of an ideal fluid in the neighborhood of bodies formed by being cut out along the streamlines of an axisymmetric flow are investigated. The flow consists of a region of isoentropic compression and a region of vortex flow. An exact solution with variable entropy is used to describe the flow in the vortex region. In the continuous flow region an approximate solution is constructed by expanding the solution in a series in a small parameter. The effect of the shape of the excision and the vorticity of the flow on compression of the jet and and the total pressure loss coefficient is studied.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77920 , NAS 1.15:77920
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Presentation of the acoustic and aerodynamic results of the Aladin 2 concept qualification testing (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Wind tunnel tests were conducted of a scale model of the Aladin 2 aircraft. The propulsion system configuration is described and the air flow caused by jet ejection is analyzed. Three dimensional flow studies in the vicinity of the engine installation were made. Diagrams of the leading and trailing edge flaps are provided. Graphs are developed to show the aerodynamic performance under conditions of various airspeed and flap deflection.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77883 , NAS 1.15:77883 , CP-143
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Discussion of the paper, Some Aspects of Propulsion for the Augmenter-Wing Concept, by D. C. Whittley (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Many modern concepts for STOL and V/STOL aircraft rely on integration of the propulsion system with the wing to create favorable lift interactions, and are known as powered lift concepts. A study of powered lift, concerning management and control of the various propulsive streams or jets is presented, each concept having its own particular objectives and requirements. Some specific objectives of this kind are described which relate to the augmentor wing. Consideration is given to three aspects of the subject, namely the augmentor flap itself, the wind ducting and augmentor primary nozzle, and the choice of powerplant or engine cycle. More generally, comments are made regarding noise attenuation and the prospect for achieving a low overall noise level for jet STOL aircraft of the future.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77884 , NAS 1.15:77884
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Periodic vortex shedding in the supersonic wake of a planar plate (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Vortex sheets in the wake have been mainly studied in incompressible flows and in the transonic region. Heinemann et al. (1976) have shown that for the subsonic region the Strouhal number is nearly independent of the Mach number. Motallebi and Norbury (1981) have observed an increase in the Strouhal number in transonic supersonic flow at Mach numbers up to 1.25. The present investigation is concerned with an extension of the studies of vortex shedding to higher supersonic Mach numbers, taking into account questions regarding the possibility of a generation of stable von Karman vortex paths in the considered Mach number range. It is found that the vortex sheet observed in a supersonic wake behind a rough plate is only stable and reproducible in cases involving a certain surface roughness and certain aspects of trailing edge geometry.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77854 , NAS 1.15:77854
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Three-dimensional unsteady lifting surface theory in the subsonic range (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The methods of the unsteady lifting surface theory are surveyed. Linearized Euler's equations are simplified by means of a Galileo-Lorentz transformation and a Laplace transformation so that the time and the compressibility of the fluid are limited to two constants. The solutions to this simplified problem are represented as integrals with a differential nucleus; these results in tolerance conditions, for which any exact solution must suffice. It is shown that none of the existing three-dimensional lifting surface theories in subsonic range satisfy these conditions. An oscillating elliptic lifting surface which satisfies the tolerance conditions is calculated through the use of Lame's functions. Numerical examples are calculated for the borderline cases of infinitely stretched elliptic lifting surfaces and of circular lifting surfaces. Out of the harmonic solutions any such temporal changes of the down current are calculated through the use of an inverse Laplace transformation.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77812 , NAS 1.15:77812 , European Aeron. Congr.; Sep 25, 1956 - Sep 29, 1956; Scheveningen; Netherlands
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Supersonic flow with feeding of energy (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The present work discusses the results of some experimental studies on the possibility of attenuating shock waves in a supersonic flow. The shock waves were formed by an external source of electrical energy. An electromechanical method is described that permits partial recovery of the expended energy.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77912 , NAS 1.15:77912
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Oscillating airfoils and their wake (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The unsteady phenomena in the wake of an oscillating wing or rotor blade are examined theoretically using the Prandtl approximation of the vortex-transport equation. A mathematical model is developed and applied to such problems as the effect of winglets on the performance of fixed wings and the possibly of employing similar designs in rotor blades. Model predictions for several profiles are compared with published and experimental measurements, and good agreement is found. Graphs and diagrams are provided.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77831 , NAS 1.15:77831 , REPT-42
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Airflow Research (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: This is an overview of research being done in laminar flow at Ames Dryden Flight Research Center and Langley Research Center. Airflow research at Ames Dryden has resulted in a special wing covering that will artificially induce laminar flow on the wing surface; this specially adapted wing is shown being tested in different flying conditions. This video also features research done at Langley in producing a chemical covering for wings that will make visible natural laminar flow and turbulent airflow patterns as they occur. Langley researchers explain possible use of this technology in supersonic flight.
    Keywords: AERODYNAMICS
    Type: ASR-239 , NASA-TM-109372 , NONP-NASA-VT-94-198219
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Unsteady aerodynamic characterization of a military aircraft in vertical gusts (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: The effects of 2.5-m/sec vertical gusts on the flight characteristics of a 1:8.6 scale model of a Mirage 2000 aircraft in free flight at 35 m/sec over a distance of 30 m are investigated. The wind-tunnel setup and instrumentation are described; the impulse-response and local-coefficient-identification analysis methods applied are discussed in detail; and the modification and calibration of the gust-detection probes are reviewed. The results are presented in graphs, and good general agreement is obtained between model calculations using the two analysis methods and the experimental measurements.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77810 , NAS 1.15:77810 , AAAF-NT-83-16 , Appl. Aerodyn. Colloq.,; Nov 08, 1983 - Nov 10, 1983; Toulouse; France
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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