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  • 1
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    Experimental techniques for three-axes load cells used at the National Full-Scale Aerodynamics Complex (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The necessary information for an aerodynamic investigation requiring load cell force measurements at the National Full-Scale Aerodynamics Complex (NFAC) is provided. Included are details of the Ames 40x80 three component load cells; typical model/load cell installation geometries; transducer signal conditioning; a description of the Ames Standard Computations Wind Tunnel Data Reduction Program for Load Cells Forces and Moments (SCELLS), and the inputs required for SCELLS. The Outdoor Aerodynamic Facilities Complex (OARF), a facility within the NFAC where three axes load cells serve as the primary balance system, is used as an example for many of the techniques, but the information applies equally well to other static and wind tunnel facilities that make use of load cell balances.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-86693 , REPT-85150 , NAS 1.15:86693
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Potential flow theory and operation guide for the panel code PMARC (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The theoretical basis for PMARC, a low-order potential-flow panel code for modeling complex three-dimensional geometries, is outlined. Several of the advanced features currently included in the code, such as internal flow modeling, a simple jet model, and a time-stepping wake model, are discussed in some detail. The code is written using adjustable size arrays so that it can be easily redimensioned for the size problem being solved and the computer hardware being used. An overview of the program input is presented, with a detailed description of the input available in the appendices. Finally, PMARC results for a generic wing/body configuration are compared with experimental data to demonstrate the accuracy of the code. The input file for this test case is given in the appendices.
    Keywords: AERODYNAMICS
    Type: NASA-TM-102851 , A-90244 , NAS 1.15:102851
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Development and validation of an advanced low-order panel method (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A low-order potential-flow panel code, PMARC, for modeling complex three-dimensional geometries, is currently being developed at NASA Ames Research Center. The PMARC code was derived from a code named VSAERO that was developed for Ames Research Center by Analytical Methods, Inc. In addition to modeling potential flow over three-dimensional geometries, the present version of PMARC includes several advanced features such as an internal flow model, a simple jet wake model, and a time-stepping wake model. Data management within the code was optimized by the use of adjustable size arrays for rapidly changing the size capability of the code, reorganization of the output file and adopting a new plot file format. Preliminary versions of a geometry preprocessor and a geometry/aerodynamic data postprocessor are also available for use with PMARC. Several test cases are discussed to highlight the capabilities of the internal flow model, the jet wake model, and the time-stepping wake model.
    Keywords: AERODYNAMICS
    Type: NASA-TM-101024 , A-88275 , NAS 1.15:101024
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Large-scale wind tunnel tests of an ejector-lift STOVL aircraft model (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The initial results of a test program conducted on an ejector-augmented-lift STOVL aircraft design in the NASA-Ames 40-by-80-Foot Wind Tunnel has established the efficient performance of this full-scale aircraft realization of the propulsion-system configuration. It has also been noted that the generation of larger lift-augmentation ratios in this form than in component tests. In addition, it is found that configurations possessing thrust/weight ratios and wing loadings representative of current practice could, when outfitted with the present propulsion scheme, produce adequate level-flight acceleration through transition from VTOL hover to wingborne flight.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 89-2905
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    High performance forward swept wing aircraft (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A high performance aircraft capable of subsonic, transonic and supersonic speeds employs a forward swept wing planform and at least one first and second solution ejector located on the inboard section of the wing. A high degree of flow control on the inboard sections of the wing is achieved along with improved maneuverability and control of pitch, roll and yaw. Lift loss is delayed to higher angles of attack than in conventional aircraft. In one embodiment the ejectors may be advantageously positioned spanwise on the wing while the ductwork is kept to a minimum.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Full-scale ground effects of twin impinging jets beneath a subsonic tactical V/STOL aircraft (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents a summary of an analysis of flow field characteristics about a large scale twin-tilt-nacelle V/STOL aircraft in close proximity to the ground. The analysis uses experimental data in the form of measurements of pressure distributions on the ground beneath the aircraft and on the undersurface of the aircraft's fuselage. The integrals of these distributions are compared with forces measured directly, for both the total model and isolated nacelles, (i.e., net thrust). The handling qualities of the vehicle were found to be influenced by flow field characteristic features, not present in simpler models. Lift increases and significant degradation in roll control occur at low heights for fuselage strake deflections of 30 degrees or more. Reductions in control effectiveness about the other axes were also observed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-2704
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Large-scale wind tunnel studies of a jet-engined powered ejector-lift STOVL aircraft (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A full-scale model of a supersonic STOVL single engine flighter aircraft employing an ejector to augment lift in hover and in low-speed flight was tested in the 40- by 80-ft and 80- by 120-ft test sections of the National Full-Scale Aerodynamics Complex located at the NASA Ames Research Center. The measured ejector augmentation ratio in hover met the design requirement of 1.6 and continued to provide the lift necessary in forward flight for good transition qualities. The up-and-away aerodynamics (ejector system stowed) were found to be conventional for this class of vehicle. The pitch control provided by the full-span blown flaps is sufficient to control the large pitching moments generated by ventral exhaust nozzle vectoring and propulsion induced aerodynamic effects such as the turning of the flow entrained into the ejectors.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: International Powered Lift Conference; Aug 29, 1990 - Aug 31, 1990; London
    Format: text
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    NASA TECHNICAL REPORTS
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