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  • 1
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    Calculation of potential flow past non-lifting bodies at angle of attack using axial and surface singularity methods (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two different singularity methods have been utilized to calculate the potential flow past a three dimensional non-lifting body. Two separate FORTRAN computer programs have been developed to implement these theoretical models, which will in the future allow inclusion of the fuselage effect in a pair of existing subcritical wing design computer programs. The first method uses higher order axial singularity distributions to model axisymmetric bodies of revolution in an either axial or inclined uniform potential flow. Use of inset of the singularity line away from the body for blunt noses, and cosine-type element distributions have been applied to obtain the optimal results. Excellent agreement to five significant figures with the exact solution pressure coefficient value has been found for a series of ellipsoids at different angles of attack. Solutions obtained for other axisymmetric bodies compare well with available experimental data. The second method utilizes distributions of singularities on the body surface, in the form of a discrete vortex lattice. This program is capable of modeling arbitrary three dimensional non-lifting bodies. Much effort has been devoted to finding the optimal method of calculating the tangential velocity on the body surface, extending techniques previously developed by other workers.
    Keywords: AERODYNAMICS
    Type: NASA-CR-166058 , NAS 1.26:166058
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Subcritical Wing Design Code (1983)
    In:  Other Sources
    Details
    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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    NASA TECHNICAL REPORTS
  • 3
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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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    NASA TECHNICAL REPORTS
  • 4
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    Computer program documentation for a subcritical wing design code using higher order far-field drag minimization (1981)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A subsonic, linearized aerodynamic theory, wing design program for one or two planforms was developed which uses a vortex lattice near field model and a higher order panel method in the far field. The theoretical development of the wake model and its implementation in the vortex lattice design code are summarized and sample results are given. Detailed program usage instructions, sample input and output data, and a program listing are presented in the Appendixes. The far field wake model assumes a wake vortex sheet whose strength varies piecewise linearly in the spanwise direction. From this model analytical expressions for lift coefficient, induced drag coefficient, pitching moment coefficient, and bending moment coefficient were developed. From these relationships a direct optimization scheme is used to determine the optimum wake vorticity distribution for minimum induced drag, subject to constraints on lift, and pitching or bending moment. Integration spanwise yields the bound circulation, which is interpolated in the near field vortex lattice to obtain the design camber surface(s).
    Keywords: AERODYNAMICS
    Type: NASA-CR-3457 , NAS 1.26:3457
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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