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  • General Chemistry  (1,738)
  • AERODYNAMICS  (1,040)
  • 1985-1989  (1,448)
  • 1975-1979  (1,330)
  • 1985  (1,448)
  • 1979  (1,330)
Collection
Keywords
Publisher
Years
  • 1985-1989  (1,448)
  • 1975-1979  (1,330)
Year
  • 1
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    On wings of circular design (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Prandtl's method of sources and sinks for air foils is used to investigate the aerodynamics of circular wings in constant flow. Lift distribution, total lift, and pitching moment are investigated as well as the influence of changes in the angle of attack.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75505
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Solution of a few nonlinear problems in aerodynamics by the finite elements and functional least squares methods (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The numerical simulation of the transonic flows of idealized fluids and of incompressible viscous fluids, by the nonlinear least squares methods is presented. The nonlinear equations, the boundary conditions, and the various constraints controlling the two types of flow are described. The standard iterative methods for solving a quasi elliptical nonlinear equation with partial derivatives are reviewed with emphasis placed on two examples: the fixed point method applied to the Gelder functional in the case of compressible subsonic flows and the Newton method used in the technique of decomposition of the lifting potential. The new abstract least squares method is discussed. It consists of substituting the nonlinear equation by a problem of minimization in a H to the minus 1 type Sobolev functional space.
    Keywords: AERODYNAMICS
    Type: NASA-TM-75732
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Aircraft icing: Introduction (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The objectives of the Workshop were as follows: (1) to assess the current understanding of fixed wing and rotorcraft operational icing environments and problems (2) to evaluate facilities requirements for R&D and certification purposes (3) to examine means of improving icing forecasts (4) to identify shortcomings in aeronautical icing knowledge which can be alleviated by new research and instrumentation development.
    Keywords: AERODYNAMICS
    Type: NASA. Lewis Res. Center Aircraft Icing; 3 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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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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  • 5
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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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  • 6
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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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  • 7
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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
  • 8
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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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  • 9
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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
  • 10
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    NASA research objectives and roles (1979)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A chronology of airfoil development is presented in order to put the present NASA airfoil program in perspective. The impact of the NACA series airfoils is considered. Development of advanced analytical and experimental methods for the design and for the determination of the characteristics of not only single element airfoils, but of multielement airfoil combinations used in aerodynamic controls and high lift systems is emphasized along with applications.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1 Pt 1; p 1-9
    Format: application/pdf
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