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  • AERODYNAMICS  (2,992)
  • 1985-1989  (2,967)
  • 1945-1949  (25)
  • 1
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    Application of a semianalytical technique for sensitivity analysis of unsteady aerodynamic computations (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: A semianalytical approach is developed for the sensitivity analysis of linear unsteady aerodynamic loads. The semianalytical approach is easier to implement than the analytical approach. It is also computationally less expensive than the finite difference approach when used with panel methods which require a large number of panels. The semianalytical approach is applied to an isolated airfoil in a two-dimensional flow and rotating propfan blades in three-dimensional flow. Sensitivity coefficients with respect to nonshape-dependent variables are shown for some cases.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-2377 , Structures, Structural Dynamics and Materials Conference; Apr 18, 1988 - Apr 20, 1988; Williamsburg, VA; United States
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  • 2
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    Some numerical calculations by using linear classical sonic theories approached from sub- or supersonic speeds (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The unsteady aerodynamics of a two-dimensional wing at sonic speed are studied by using so-called classical sonic theories (linear), approached from supersonic flow (M=1+0) or subsonic flow (M=1-0). In the former approach, the exact expressions of lift and lift distribution are obtained in terms of Fresnel integrals, while in the latter approach an integral equation must be solved, the kernel function of which is obtained from the subsonic Possio's equation and has a root singularity. The discrete analysis is adopted on the basis of the semicircle method (SCM) and the weighting function for subsonic-flow-Gauss-quadrature, as well as modified characteristics obtained from both approaches agree quite well with each other. The results obtained by the present computations are compared with those of DLM-C (subsonic 2D code) developed by ANDO et al, and are found to give a reasonable outer boundary for subsonic unsteady aerodynamics.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20112 , NAS 1.77:20112
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  • 3
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    The Aerodynamic Optimization of Wings at Subsonic Speeds and the Influence of Wingtip Design (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Some of the objectives of modern aircraft development are related to the achievement of reduced fuel consumption and aircraft noise. This investigation is mainly concerned with the aerodynamic aspects of aircraft development, i.e., reduction of induced drag. New studies of wing design, and in particular wing tips, are considered. Induced drag is important since, in cruising flight, it accounts for approximately one-third of the entire drag for the aircraft, and one-half while climbing. A survey is presented for the wing geometries and wing tip designs studied, and theoretical investigations of different planar wings with systematically varied wing tip forms are conducted. Attention is also paid to a theoretical study of some planar and nonplanar wings and their comparison with experimental data.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88534 , NAS 1.15:88534
    Format: application/pdf
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  • 4
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    Aeronautical engineering: A continuing bibliography with indexes (supplement 225) (1988)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This bibliography lists 429 reports, articles, and other documents introduced into the NASA scientific and technical information system in March, 1988.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(225) , NAS 1.21:7037(225)
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  • 5
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    Finite element calculations for aerodynamic coefficients of a 3-dimensional body in subsonic flow using Green's function method (1988)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An accurate method for evaluating the derivatives along circular paths on the surface is proposed. Calculations are made on various practical configurations such as wing-body combinations, tandem wings, wings with dihedral angles at sideslip, ground effects, interference between a sphere and wind tunnel, etc. Comparisons with experiment show good agreement.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20208 , NAS 1.77:20208
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  • 6
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    Calculation of non-stationary aerodynamic forces in the near sonic range (1988)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The development of a mathematical method for calculating nonstationary supersonic flow in the near-sonic range is described. A perturbation formula is derived based on the exact stationary values; it is applicable to the equation for potential. The problem can thus be divided into stationary and nonstationary fields. The pressure distribution in an oscillating profile is determined, based on hyperbolic differential equations. It is shown that there are important corollaries concerning the application of linear theory. With suitable extrapolations, linear theory can be used up to about Mach 0.8. Linear theory is not applicable, however, when determining the moment coefficients; for this case, a special technique is described.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20310 , NAS 1.77:20310
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  • 7
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    Aeronautical engineering: A continuing bibliography with indexes (supplement 219) (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This bibliography lists 586 reports, articles, and other documents introduced into the NASA scientific and technical information system in October, 1987.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(219) , NAS 1.21:7037(219)
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  • 8
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    Calculation of aerodynamic heat transfer for blunt-nosed thin wings at different angles of attack at supersonic speeds (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A method for calculating aerodynamic heat transfer on thin wings at angles of attack is provided, based on the assumption of small cross flow and the calculation of an infinite cylinder. It is valid in the range of supersonic and hypersonic speeds. The method does not require calculation of the details of the stream lines and can be used for various swept wings at moderate angle of attack or yaw angle. A comparison between theoretical and experimental results is given.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20127 , NAS 1.77:20127
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  • 9
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    Calculation of the distributed loads on the blades of individual multiblade propellers in axial flow using linear and nonlinear lifting surface theories (1988)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: In recent years much attention has been given to the development of methods and programs for the calculation of the aerodynamic characteristics of multiblade, saber-shaped air propellers. Most existing methods are based on the theory of lifting lines. Elsewhere, the theory of a lifting surface is used to calculate screw and lifting propellers. In this work, methods of discrete eddies are described for the calculation of the aerodynamic characteristics of propellers using the linear and nonlinear theories of lifting surfaces.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20173 , NAS 1.77:20173 , (ISSN 0321-3429)
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  • 10
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    Aeronautical engineering: A cumulative index to a continuing bibliography (1988)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: This bibliography is a cumulative index to the abstracts contained in NASA SP-7037(210) through NASA SP-7037(221) of Aeronautical Engineering: A Continuing Bibliography. NASA SP-7037 and its supplements have been compiled through the cooperative efforts of the American Institute of Aeronautics and Astronautics (AIAA) and the National Aeronautics and Space Administration (NASA). This cumulative index includes subject, personal author, corporate source, foreign technology, contract number, report number, and accession number indexes.
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(222) , NAS 1.21:7037(222)
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  • 11
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    The interference of the model support mast with measurements of the longitudinal and lateral aerodynamic coefficients (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The effects the single-bottom support masts used in the ONERA S1 and S4 wind tunnels have on aerodynamic data collected with scale model aircraft were examined experimentally and analytically. Systematic studies were performed on the flow characteristics around different diameters for the mounts. Scaling methods used to make data from one wind tunnel correspond to data from the other are described. Airbus 320 models were introduced into the tests and mast-body flow interactions were observed. A summary is presented of restrictions on the mast diameters, relative to cylindrical model diameters, which will minimize the effects the masts have on longitudinal and lateral aerodynamic stability data.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20079 , NAS 1.77:20079 , ONERA-TP-1986-181
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  • 12
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    Hypersonic aerodynamic coefficients and convection flow estimation in a HERMES type project (1987)
    In:  CASI
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    Publication Date: 2019-08-28
    Description: An analysis of all the experimental and computation requirements of the HERMES project is presented. The discussion includes the influence of the upper atmosphere composition and possible chemical reactions, the information collected in Orbiter experiments, the possibility of utilizing plasma generators and CF4 in wind tunnel tests, the development of parabolized Navier-Stokes models and solutions, and the computing capacity requirements.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20019 , NAS 1.77:20019
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  • 13
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    Aerodynamics of the Viggen 37 aircraft. Part 1: General characteristics at low speed (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A description of the aerodynamics of the Viggen 37 and its performances, especially at low speeds is presented. The aerodynamic requirements for the design of the Viggen 37 aircraft are given, including the basic design, performance requirement, and aerodynamic characteristics, static and dynamic load test results and flight test results. The Viggen 37 aircraft is designed to be used for air attack, surveillance, pursuit, and training applications. It is shown that this aircraft is suitable for short runways, and has good maneuvering, acceleration, and climbing characteristics. The design objectives for this aircraft were met by utilizing the effect produced by the interference between two triangular wings, positioned in tandem.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88403 , NAS 1.15:88403
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  • 14
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    Formation of asymmetric separated flow past slender bodies of revolution at large angles of attack (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The paper examines the problem of determining stationary positions of pairs of vortices of unequal intensity in the flow behind a cylinder modeling the axisymmetric separated flow past a slender body at large angles of attack. The possible asymmetric stationary positions of two vortices are calculated, and their stability with respect to small perturbations is determined. Bifurcations of the flow field with changes in vortex intensity are analyzed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88441 , NAS 1.15:88441 , (ISSN 0321-3249)
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  • 15
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    Mutual effect of thermochemical surface decomposition and viscous interaction during hypersonic flow past a sharp cone (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Numerical results on the hypersonic gas flow in viscous interaction regime past sharp circular cones with thermally destructible Teflon surface are presented. Characteristics of the mutual influence between the thermochemical decomposition of the surface and the viscous interaction are revealed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78015 , NAS 1.15:78015
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  • 16
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    Three-dimensional boundary layer analysis program Blay and its application (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The boundary layer calculation program (BLAY) is a program code which accurately analyzes the three-dimensional boundary layer of a wing with an undefined plane. In comparison with other preexisting programs, the BLAY is characterized by the following: (1) the time required for computation is shorter than any other; (2) the program is adaptable to a parallel processing computer; and (3) the program is associated with a secondary accuracy in the z-direction. As a boundary layer modification to transonic nonviscous flow analysis programs, it is used to adjust viscous and nonviscous interference problems repeatedly. Its efficiency is an important factor in cost reduction in aircraft designing.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77962 , NAS 1.15:77962 , Jun 30, 1983 - Jul 01, 1983; Tokyo; Japan
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  • 17
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    Comparison of computational results of a few representative three-dimensional transonic potential flow analysis programs (1986)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The development of transonic aerodynamic computation methods and specific examples, as well as examples of three-dimensional transonic computation in design, are discussed. The case of the transonic transport and the case of the small transport are analyzed. Requirements for programs of the future are itemized.
    Keywords: AERODYNAMICS
    Type: NASA-TM-77963 , NAS 1.15:77963 , Jun 30, 1983 - Jul 01, 1983; Tokyo; Japan
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  • 18
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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
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  • 19
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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
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  • 20
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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
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