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  • AERODYNAMICS  (7)
  • 1990-1994  (7)
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Year
  • 1
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    Automatic computation of Euler-marching and subsonic grids for wing-fuselage configurations (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Algebraic procedures are described for the automatic generation of structured, single-block flow computation grids for relatively simple configurations (wing, fuselage, and fin). For supersonic flows, a quasi two-dimensional grid for Euler-marching codes is developed, and some sample results in graphical form are included. A type of grid for subsonic flow calculation is also described. The techniques are algebraic and are based on a generalization of the method of transfinite interpolation.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4573 , L-17364 , NAS 1.15:4573
    Format: application/pdf
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  • 2
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    Automatic procedures for computing complete configuration geometry from individual component descriptions (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Procedures are derived for developing a complete airplane surface geometry starting from component descriptions. The procedures involve locating the intersection lines of adjacent components and omitting any regions for which part of one surface lies within the other. The geometry files utilize the wave-drag (Harris) format, and output files are written in Hess format. Two algorithms are used: one, if both intersecting surfaces have airfoil cross sections; the other, if one of the surfaces has circular cross sections. Some sample results in graphical form are included.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4607 , L-17395 , NAS 1.15:4607
    Format: application/pdf
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  • 3
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    Automatic computation of wing-fuselage intersection lines and fillet inserts with fixed-area constraint (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Procedures for automatic computation of wing-fuselage juncture geometry are described. These procedures begin with a geometry in wave-drag format. First, an intersection line is computed by extrapolating the wing to the fuselage. Then two types of filleting procedures are described, both of which utilize a combination of analytical and numerical techniques appropriate for automatic calculation. An analytical technique for estimating the added volume due to the fillet is derived, and an iterative procedure for revising the fuselage to compensate for this additional volume is given. Sample results are included in graphical form.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4406 , L-17131 , NAS 1.15:4406
    Format: application/pdf
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  • 4
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    Trajectory fitting in function space with application to analytic modeling of surfaces (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A theory for representing a parameter-dependent function as a function trajectory is described. Additionally, a theory for determining a piecewise analytic fit to the trajectory is described. An example is given that illustrates the application of the theory to generating a smooth surface through a discrete set of input cross-section shapes. A simple procedure for smoothing in the parameter direction is discussed, and a computed example is given. Application of the theory to aerodynamic surface modeling is demonstrated by applying it to a blended wing-fuselage surface.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3232 , L-17054 , NAS 1.60:3232
    Format: application/pdf
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  • 5
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    A method for designing blended wing-body configurations for low wave drag (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A procedure for tailoring a blended wing-body configuration to reduce its computed wave drag is described. The method utilizes an iterative algorithm within the framework of first-order linear theory. Four computed examples are included. In each case, the zero-lift wave drag was reduced without an increase in the drag due to lift.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3261 , L-17095 , NAS 1.60:3261
    Format: application/pdf
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  • 6
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    Comparison of jet plume shape predictions and plume influence on sonic boom signature (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An Euler shock-fitting marching code yields good agreement with semiempirically determined plume shapes, although the agreement decreases somewhat with increasing nozzle angle and the attendant increase in the nonisentropic nature of the flow. Some calculations for the low boom configuration with a simple engine indicated that, for flight at altitudes above 60,000 feet, the plume effect is dominant. This negates the advantages of a low boom design. At lower altitudes, plume effects are significant, but of the order that can be incorporated into the low boom design process.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3172 , L-16970 , NAS 1.60:3172
    Format: application/pdf
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  • 7
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    Diffracted and head waves associated with waves on nonseparable surfaces (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A theory is presented for computing waves radiated from waves on a smooth surface. With the assumption that attention of the surface wave is due only to radiation and not to dissipation in the surface material, the radiation coefficient is derived in terms of the attenuation factor. The excitation coefficient is determined by the reciprocity condition. Formulas for the shape and the spreading of the radiated wave are derived, and some sample calculations are presented. An investigation of resonant phase matching for nonseparable surfaces is presented with a sample calculation. A discussion of how such calculations might be related to resonant frequencies of nonseparable thin shell structures is included. A description is given of nonseparable surfaces that can be modeled in the vector that facilitates use of the appropriate formulas of differential geometry.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3169 , L-16968 , NAS 1.60:3169
    Format: application/pdf
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