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  • 1
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    Robichek and Myers, "Optimal Financing Decisions" (Book Review) (1967)
    Menasha, Wis. : Periodicals Archive Online (PAO)
    The Accounting Review. 42:1 (1967:Jan.) 218 
    Details
    ISSN: 0001-4826
    Topics: Economics
    Description / Table of Contents: BOOK REVIEWS, CHARLES H. GRIFFIN, Editor
    Notes: Departments
    URL: http://gateway.proquest.com/openurl?url_ver=Z39.88-2004&res_dat=xri:pao:&rft_dat=xri:pao:article:5030-1967-042-01-000039
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Higher order farfield drag minimization for a subcritical wing design code (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: A higher order Trefftz plane model of the undistorted interacting wing wakes of two symmetric subsonic planforms has been developed and integrated with an existing vortex lattice wing design code. The Trefftz plane calculation provides continuous, piecewise quadratically varying bound circulations, which are then interpolated in the nearfield vortex lattice representation of the wing. Integration of the surface slopes for a specified chord loading function provides the design wing camber surfaces. This paper outlines the theoretical development and presents comparisons between results obtained using the present theory and (1) previous exact solutions for minimum induced drag and (2) previous wing designs obtained using a discrete vortex wake moded.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 17; Sept
    Format: text
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  • 3
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    Jet decay rate effects on hover jet-induced loads (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The paper explains the mechanisms for observed jet decay rate effects on jet-induced loads on a flat plate for cross-flow and hover configurations. Examples are presented for the influence of the decay rate on integrated loads on a flat plate induced by the jet issuing at a right angle from the plate into still air; knowledge of these jet-induced loadings is of particular importance for VTOL aircraft design because they produce an effective loss in the lift force available in hover. The apparent inconsistency between existing lift loss vs jet decay rate trends is explained in light of the different mechanism which determine the jet mixing and trajectory, i.e., entrainment, blockage, and the vortex pair associated with a jet in crossflow.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 17; Aug. 198
    Format: text
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  • 4
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    Optimized aerodynamic design process for subsonic transport wing fitted with winglets (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The aerodynamic design of a wind-tunnel model of a wing representative of that of a subsonic jet transport aircraft, fitted with winglets, was performed using two recently developed optimal wing-design computer programs. Both potential flow codes use a vortex lattice representation of the near-field of the aerodynamic surfaces for determination of the required mean camber surfaces for minimum induced drag, and both codes use far-field induced drag minimization procedures to obtain the required spanloads. One code uses a discrete vortex wake model for this far-field drag computation, while the second uses a 2-D advanced panel wake model. Wing camber shapes for the two codes are very similar, but the resulting winglet camber shapes differ widely. Design techniques and considerations for these two wind-tunnel models are detailed, including a description of the necessary modifications of the design geometry to format it for use by a numerically controlled machine for the actual model construction.
    Keywords: AERODYNAMICS
    Type: NASA-CR-159180
    Format: application/pdf
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  • 5
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    Subcritical Wing Design Code (1983)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: QUICK Interactive Graphics Analysis program, QUIAGA, displays aircraft QUICK-geometry data to aid in detection and analysis of errors. Program generates completely-analytical aircraft geometry description for use by finite difference flow codes. QUIAGA written in FORTRAN IV.
    Keywords: MECHANICS
    Type: LAR-12959 , NASA Tech Briefs (ISSN 0145-319X); 7; 4; P. 437
    Format: text
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  • 6
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    Potential flow past axisymmetric bodies at angle of attack (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The Karamcheti (1966) suggestion concerning the use of higher order singularity techniques has been developed for the calculation of incompressible flow past an axisymmetric body at angle of attack. Attention is given to the results of a convergence study using this axial singularity method, where solution accuracy has been investigated for ellipsoids of slenderness ratio in the 1-10 range for both axial and inclined flow. Effects of singularity type, element number and size distribution, and singularity line inset distance, are noted, and a paneling scheme is developed which yields accurate results for the class of axisymmetric bodies having continuous body slopes with discontinuous curvature jumps.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 21; 218-220
    Format: text
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  • 7
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    Experimental investigation of effect of jet decay rate on jet-induced pressures on a flat plate (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental study of the interaction between a lift jet and an aircraft wing for a jet VTOL aircraft was performed for the simplified model of an unheated, subsonic, circular jet exiting at right angles to a flat plate into a uniform subsonic crosswind. The effects of jet dynamic pressure decay rate upon the jet location and jet induced pressure distribution on the plate were studied over a range of jet to crossflow velocity ratios of 2.2 or = R or = 10. Jet decay rate was varied through use of cylindrical centerbodies with flat or hemispherical tips submerged in the jet nozzle at various depths below the jet exit plane. Quicker jet dynamic pressure decay, caused by the presence of a centerbody, resulted in reductions in the jet induced lift loss by as much as 45 percent relative to values for jets with no centerbody. These reductions in lift loss were observed at the larger values of crossflow velocity.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-2979
    Format: application/pdf
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  • 8
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    Winglet effectiveness on low aspect ratio wings at supersonic Mach numbers (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A computational study has been conducted on two wings of aspect ratios 1.244 and 1.865, each having 65-deg leading edge sweep angles, to determine the effects of nonplanar winglets at supersonic Mach numbers. A design Mach number of 1.62 was selected. The winglets studied were parametrically varied in alignment, length, sweep, camber, and thickness to determine the effects of winglet geometry on predicted performance. For the computational analysis, an existing Euler code that employed a marching technique was used. The results indicated that the possibility existed for wing-winglet geometries to equal the performance of wing-alone bodies in supersonic flows with both bodies having the same semispan length. The performance parameters of main interest were the lift-to-pressure drag ratio and the pressure drag coefficient as functions of lift coefficient. The lift coefficient range for this study was from -0.20 to 0.70 with emphasis on the range of 0.10 to 0.22.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-3305 , AIAA Applied Aerodynamics Conference; Sept. 23-25, 1991; Baltimore, MD; United States
    Format: text
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  • 9
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    Analytical studies of separated vortex flow on highly swept wings (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A subsonic potential flow mathematical model of the flow past slender aerodynamic surfaces with sharp edges and separated vortex flow is reported. Comparisons with experimental data are presented for overall forces and pressure distributions for a series of thin, low aspect ratio wings, including both flat and conically cambered ones. A discussion is presented of the limitations of the current theory, and some suggestions are made as to how the theory might be improved. Details of program data input modifications for three-dimensional geometry are described in an appendix.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3022
    Format: application/pdf
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  • 10
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    Iterative optimal subcritical aerodynamic design code including profile drag (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A subcritical aerodynamic design computer code has been developed, which uses linearized aerodynamics along with sweep theory and airfoil data to obtain minimum total drag preliminary designs for multiple planform configurations. These optimum designs consist of incidence distributions yielding minimum total drag at design values of Mach number and lift and pitching moment coefficients. Linear lofting is used between airfoil stations. Solutions for isolated transport wings have shown that the solution is unique, and that including profile drag effects decreases tip loading and incidence relative to values obtained for minimum induced drag solutions. Further, including effects of variation of profile drag with Reynolds number can cause appreciable changes in the optimal design for tapered wings. Example solutions are also discussed for multiple planform configurations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-0012 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
    Format: text
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