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  • 1
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    WAVDRAG- ZERO-LIFT WAVE DRAG OF COMPLEX AIRCRAFT CONFIGURATIONS (1994)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: WAVDRAG calculates the supersonic zero-lift wave drag of complex aircraft configurations. The numerical model of an aircraft is used throughout the design process from concept to manufacturing. WAVDRAG incorporates extended geometric input capabilities to permit use of a more accurate mathematical model. With WAVDRAG, the engineer can define aircraft components as fusiform or nonfusiform in terms of non-intersecting contours in any direction or more traditional parallel contours. In addition, laterally asymmetric configurations can be simulated. The calculations in WAVDRAG are based on Whitcomb's area-rule computation of equivalent-bodies, with modifications for supersonic speed. Instead of using a single equivalent-body, WAVDRAG calculates a series of equivalent-bodies, one for each roll angle. The total aircraft configuration wave drag is the integrated average of the equivalent-body wave drags through the full roll range of 360 degrees. WAVDRAG currently accepts up to 30 user-defined components containing a maximum of 50 contours as geometric input. Each contour contains a maximum of 50 points. The Mach number, angle-of-attack, and coordinates of angle-of-attack rotation are also input. The program warns of any fusiform-body line segments having a slope larger than the Mach angle. WAVDRAG calculates total drag and the wave-drag coefficient of the specified aircraft configuration. WAVDRAG is written in FORTRAN 77 for batch execution and has been implemented on a CDC CYBER 170 series computer with a central memory requirement of approximately 63K (octal) of 60 bit words. This program was developed in 1983.
    Keywords: AERODYNAMICS
    Type: LAR-13223
    Format: text
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  • 2
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    A computer program for fitting smooth surfaces to three-dimensional aircraft configurations (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A computer program developed to fit smooth surfaces to the component parts of three-dimensional aircraft configurations was described. The resulting equation definition of an aircraft numerical model is useful in obtaining continuous two-dimensional cross section plots in arbitrarily defined planes, local tangents, enriched surface plots and other pertinent geometric information; the geometry organization used as input to the program has become known as the Harris Wave Drag Geometry.
    Keywords: COMPUTER OPERATIONS AND HARDWARE
    Type: Appl. of Computer Graphics in Eng.; p 569-586
    Format: application/pdf
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  • 3
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    Theoretical boundaries and internal characteristics of exhaust plumes from three different supersonic nozzles (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Exhaust plume boundaries and internal characteristics in rocket exhaust plumes calculated for three different supersonic nozzles
    Keywords: FLUID MECHANICS
    Type: NASA-TN-D-2650
    Format: application/pdf
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  • 4
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    Comparisons of Experimental Free-jet Boundaries with Theoretical Results Obtained with the Method of Characteristics (1964)
    In:  CASI
    Details
    Publication Date: 2019-05-21
    Description: Highly underexpanded free jet boundary contours
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: NASA-TN-D-2327
    Format: application/pdf
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  • 5
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    A description of the Langley wireframe geometry standard (LaWGS) format (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The background leading to the adoption of a Langley Research Center wireframe geometry format standard, a detailed description of the standard, and recommendations for use of the standard is given. The standard chosen is flexible enough to describe almost any complex shape.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85767 , Z-2 , NAS 1.15:85767
    Format: application/pdf
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  • 6
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    User's guide for a computer program for calculating the zero-lift wave drag of complex aircraft configurations (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A computer program was developed to extend the geometry input capabilities of previous versions of a supersonic zero lift wave drag computer program. The arbitrary geometry input description is flexible enough to describe almost any complex aircraft concept, so that highly accurate wave drag analysis can now be performed because complex geometries can be represented accurately and do not have to be modified to meet the requirements of a restricted input format.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-TM-85670 , L-15603 , NAS 1.15:85670
    Format: application/pdf
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  • 7
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    Zero-Lift Wave Drag of Complex Aircraft Configurations (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: WAVDRAG calculates supersonic zero-lift wave drag of complex aircraft configurations. Numerical model of aircraft used throughout design process from concept to manufacturing. Incorporates extended geometric input capabilities to permit use of more accurate mathematical model. Engineer defines aircraft components as fusiform or nonfusiform in terms of traditional parallel contours or nonintersecting contours in any direction. Laterally asymmetric configurations simulated. WAVDRAG calculates total drag and wave-drag coefficient of specified aircraft configuration.
    Keywords: MECHANICS
    Type: LAR-13223 , NASA Tech Briefs (ISSN 0145-319X); 9; 4; P. 150
    Format: text
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  • 8
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    Program computes zero lift wave drag of entire aircraft (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Computer program computes zero lift wave drag of an entire aircraft including any combination of the wing, body, pods, fins, and carnard. The program computes the external volume of the wing and the axial area distribution of the wing equivalent body.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LAR-10079
    Format: application/pdf
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  • 9
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    Computer program calculates sonic-boom pressure signatures (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Computer programs calculate sonic boom characteristics of airplane configurations for a range of flight conditions. One program provides the area distribution, and another program provides the equivalent area due to lift. Program outputs are the complete near field /or far field/ pressure signature, including shock wave strengths and locations.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: LAR-10096
    Format: application/pdf
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  • 10
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    A computer program for fitting smooth surfaces to an aircraft configuration and other three dimensional geometries (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computer program that uses a three-dimensional geometric technique for fitting a smooth surface to the component parts of an aircraft configuration is presented. The resulting surface equations are useful in performing various kinds of calculations in which a three-dimensional mathematical description is necessary. Programs options may be used to compute information for three-view and orthographic projections of the configuration as well as cross-section plots at any orientation through the configuration. The aircraft geometry input section of the program may be easily replaced with a surface point description in a different form so that the program could be of use for any three-dimensional surface equations.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA-TM-X-3206 , L-9934
    Format: application/pdf
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