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  • Organic Chemistry  (684)
  • Inorganic Chemistry  (658)
  • AERODYNAMICS  (629)
  • 1985-1989  (1,971)
  • 1987  (1,971)
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Keywords
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Years
  • 1985-1989  (1,971)
Year
  • 1
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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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  • 2
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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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  • 3
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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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  • 4
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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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  • 5
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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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  • 6
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    Hypersonic aerodynamic coefficients and convection flow estimation in a HERMES type project (1987)
    In:  CASI
    Details
    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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  • 7
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    Stability characteristics of a supersonic boundary layer and their relation to the position of the laminar-turbulent transition point (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: By comparing the calculated results with experimental data, it is demonstrated that the position of the laminar-boundary transition point of a boundary layer can be estimated by using the e-exp-n method. The effect of the Mach number, pressure gradient, and heat transfer on the laminar-turbulent transition is discussed. It is found that under conditions of strong cooling, the effect of the pressure gradient on the position of the transition point is less pronounced than in the absence of heat transfer.
    Keywords: AERODYNAMICS
    Type: NASA-TM-88533 , NAS 1.15:88533
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  • 8
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    Development of supersonic computational aerodynamic program using panel method (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: An aerodynamic program for steady supersonic linearized potential flow using a higher order panel method was developed. Boundary surface is divided into planar triangular panels on each of which a linearly varying doublet and a constant or linearly varying source are distributed. Distributions of source and doublet on the panel assemblies of the panels can be determined by their strengths at nodal points, which are placed at the vertices of the panels for linear distribution or on each panel for constant distribution.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20113 , NAS 1.77:20113
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  • 9
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    Integral method of wall interference correction in low-speed wind tunnels (1987)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The analytical solution of Poisson's equation, derived form the definition of vortex, was applied to the calculation of interference velocities due to the presence of wind tunnel walls. This approach, called the Integral Method, allows an accurate evaluation of wall interference for separated or more complicated flows without the need for considering any features of the model. All the information necessary for obtaining the wall correction is contained in wall pressure measurements. The correction is not sensitive to normal data-scatter, and the computations are fast enough for on-line data processing.
    Keywords: AERODYNAMICS
    Type: NASA-TT-20055 , NAS 1.77:20055
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  • 10
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    Use of LEBU-devices for drag reduction at flight conditions (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The practical aspects of drag reduction using LEBU (large-eddy break-up) devices, turbulence manipulators, etc. in flight are discussed with the help of experience from previous flight tests. These tests have shown that appreciable reductions in local skin friction exist under flight conditions, and that the turbulence-manipulating effects can be found for swept tandem devices in transonic as well as supersonic flows. The unsteady loads experienced with the devices are discussed in connection with the frequencies occurring in this type of real flight conditions.
    Keywords: AERODYNAMICS
    Type: Turbulent drag reduction by passive means; Sept. 15-17, 1987; London
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  • 11
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    Modification of turbulent boundary layer structure by large-eddy breakup devices (1987)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: The modification of the turbulent boundary layer large-eddy structure by streamlined devices is analyzed using the rapid distortion approximation and unsteady aerodynamic theory. The fluctuating velocity downstream of thin plate and airfoil-shaped devices is calculated throughout the boundary layer for two-dimensional and three-dimensional upstream harmonic disturbances. It is shown that such devices suppress most effectively the fluctuating vertical velocity for a range of reduced frequencies k(1) based on the device chord length. This effect depends on the device geometry and loading, its distance to the wall, and on the upstream disturbance condition. Effective devices suppressing most of the large-scale turbulent energy are such that k(1) varies over the 0.5 to 3.0 range. For airfoil-shaped devices, the device thickness has minimal effect on its performance. On the other hand, lifting devices are more effective than thin plates particularly for two-dimensional disturbances.
    Keywords: AERODYNAMICS
    Type: Turbulent drag reduction by passive means; Sept. 15-17, 1987; London
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  • 12
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    Turbulent drag reduction research at NASA Langley - Progress and plans (1987)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: Prospective research efforts planned at NASA-Langley in view of results obtained to date in passive turbulent drag reduction experiments are discussed. It has been established that conventional flow-aligned riblets are effective even in the presence of a degree of flow inclination and pressure gradients, and at transonic speeds. No increase in net drag reduction is expected from nonconventional riblet geometries. Large eddy breakup devices promise drag reductions in the 8-15 percent range. Heat transfer-augmentation, noise-reduction, turboprop/fuselage interaction noise reduction, are other advantages expected from this line of research.
    Keywords: AERODYNAMICS
    Type: Turbulent drag reduction by passive means; Sept. 15-17, 1987; London
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  • 13
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    Three-dimensional stability of boundary layers (1987)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: The most recent efforts on the stability and transition of three-dimensional flows are reviewed. These include flows over swept wings, rotating disks, rotating cones, yawed bodies, corners, and attachment lines. The generic similarities of their stability behavior is discussed. It is shown that the breakdown process is very complex, often leading to contradictory results. Particular attention is paid to opposing observations of stationary and traveling wave disturbances.
    Keywords: AERODYNAMICS
    Type: Perspectives in turbulence studies; May 11, 12, 1987; Goettingen; Germany
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  • 14
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    Detection of large-scale organized motions in a turbulent boundary layer (1987)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: This paper presents and discusses experimental data from an investigation of organized motions in a supersonic turbulent boundary layer. Conditional sampling of crossed-wire and multiple normal-wire signals is performed. A comparison is made between events detected using the VITA conditional sampling technique and those found by thresholding the UV signal. Based on this comparison, limitations of the VITA technique are discussed. The conditional sampling results indicate that most organized motions are consistent with hairpin vortices.
    Keywords: AERODYNAMICS
    Type: Symposium on Turbulent Shear Flows; Sept. 7-9, 1987; Toulouse; France
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  • 15
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    Reynolds shear stress development in pressure-driven three-dimensional turbulent boundary-layers (1987)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: The development of the Reynolds stresses has been examined experimentally in an initially two-dimensional boundary layer which is driven to three dimensionality by a spanwise pressure gradient. The pressure field was imposed by an upstream-facing wedge. Two different wedge angles were used in order to vary the level of boundary layer skewing. Bradshaw's Al parameter was found to decrease with the rate of decrease being dependent on the level of skewing between the freestream and the wall flow. It was also concluded that the ratio of the cross-stream to streamwise shear stress components was governed by the rate of freestream turning.
    Keywords: AERODYNAMICS
    Type: Symposium on Turbulent Shear Flows; Sept. 7-9, 1987; Toulouse; France
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  • 16
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    Flow in out-of-plane double S-bends (1987)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: An experimental investigation of developing flows through a combination of out-of-plane S-bend ducts was conducted to gain insight into the redirection of flow in geometries similar to those encountered in practical aircraft wing-root intake ducts. The present double S-bend was fabricated by placing previously investigated S-ducts and S-diffusers in series and with perpendicular planes of symmetry. Laser-Doppler anemometry was employed to measure the three components of mean velocity, the corresponding rms quantities, and Reynolds stresses in the rectangular cross-section ducts. Due to limited optical access, only two mean and rms velocity components were resolved in the circular cross-section ducts. The velocity measurements were complemented by wall static pressure measurements. The data indicates that the flows at the exit are complex and asymmetric. Secondary flows generated by the pressure field in the first S-duct are complemented or counteracted by the secondary flows produced by the area expansion and the curvature of the S-diffuser. The results indicate the dominance of the inlet conditions and geometry upon the development of secondary flows and demonstrate that the flows are predominantly pressure-controlled. The pressure distribution caused by the duct geometry determines the direction and magnitude of the bulk flow while the turbulence dictates the mixing characteristics and profiles in the near wall region.
    Keywords: AERODYNAMICS
    Type: Symposium on Turbulent Shear Flows; Sept. 7-9, 1987; Toulouse; France
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  • 17
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    Properties of a half-delta wing vortex (1987)
    In:  Other Sources
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    Publication Date: 2019-07-27
    Description: The mean flow and turbulence structure of a single longitudinal vortex generated by a half-delta wing placed at a small angle of attack were investigated. Particular consideration was given to the near-field properties of the generator in order to establish the role of the generator wake in the initial rolling-up of the vortex, as well as to the far-field properties so that the approach to equilibrium could be studied. Measurements were made on fine cross-plane grids at seven streamwise locations using hot cross wires. The results show that the point of maximum vorticity and the generator wake do not merge until a streamwise distance equivalent to three generator heights is reached. Comparison with previous data on vortices produced by double-branched generators confirmed that the present vortex had achieved a fully developed state, and at a relatively short streamwise distance.
    Keywords: AERODYNAMICS
    Type: Symposium on Turbulent Shear Flows; Sept. 7-9, 1987; Toulouse; France
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  • 18
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    An assessment of upper surface blowing for the reduction of tilt rotor download (1987)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A study evaluating the use of upper-surface blowing to reduce the wing download on a V-22 tilt rotor aircraft has been completed. The study assesses the penalties associated with the upper-surface blowing system (compressor weight, compressor power, etc.), and the reduction in wing download, for a wide range of blowing slot heights and blowing pressure ratios. Three wing configurations were investigated: blowing at both leading and trailing edges with no change in wing planform relative to the V-22 tilt rotor aircraft, blowing at both leading and trailing edges with a 25% reduction in wing chord, and blowing at the leading edge only with the flap deflected 75 deg. Predicted download is presented for all of these configurations, and is compared with the download of the baseline V-22 tilt rotor aircraft configuration. The optimum configuration had 15% less net download than the baseline V-22 configuration.
    Keywords: AERODYNAMICS
    Type: ; 9 p.|Aug 01, 1987; Monterey, CA; United States
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  • 19
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    Research in Natural Laminar Flow and Laminar-Flow Control, part 3 (1987)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Part 3 of the Symposium proceedings contains papers addressing advanced airfoil development, flight research experiments, and supersonic transition/laminar flow control research. Specific topics include the design and testing of natural laminar flow (NLF) airfoils, NLF wing gloves, and NLF nacelles; laminar boundary-layer stability over fuselage forebodies; the design of low noise supersonic/hypersonic wind tunnels; and boundary layer instability mechanisms on swept leading edges at supersonic speeds.
    Keywords: AERODYNAMICS
    Type: NASA-CP-2487-PT-3 , L-16350-PT-3 , NAS 1.55:2487-PT-3 , Mar 16, 1987 - Mar 19, 1987; Hampton, VA; United States
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  • 20
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    Research in Natural Laminar Flow and Laminar-Flow Control, part 2 (1987)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Part 2 of the Symposium proceedings includes papers addressing various topics in basic wind tunnel research/techniques and computational transitional research. Specific topics include: advanced measurement techniques; laminar flow control; Tollmien-Schlichting wave characteristics; boundary layer transition; flow visualization; wind tunnel tests; flight tests; boundary layer equations; swept wings; and skin friction.
    Keywords: AERODYNAMICS
    Type: NASA-CP-2487-PT-2 , L-16350-PT-2 , NAS 1.55:2487-PT-2 , Mar 16, 1987 - Mar 19, 1987; Hampton, VA; United States
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