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  • Other Sources  (7)
  • 1
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    Supersonic STOVL fighter concepts featuring the hybrid tandem-fan propulsion system (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Current research on vertical- or short-takeoff-and-landing (V/STOL) aircraft is concentrating on developing a multirole-capable fighter. Several V/STOL concepts being studied show a capability performing for short-takeoff and vertical-landing (STOVL) missions. This paper is concerned with a propulsion concept which promises added flexibility in mission performance: the hybrid-tandem fan. This propulsion concept is combined with four aircraft planforms and the performance of each is evaluated on a representative mission. The four aircraft planforms used in the study are a conventional wing-tail, a forward-swept wing and canard, a delta-wing and canard, and an oblique wing and tail. The mission was chosen so that the four aircraft all had approximately the same gross takeoff weight. The four designs are compared at various phases of the mission.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
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    NASA TECHNICAL REPORTS
  • 2
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    ACSYNT - A standards-based system for parametric, computer aided conceptual design of aircraft (1992)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A group of eight US aerospace companies together with several NASA and NAVY centers, led by NASA Ames Systems Analysis Branch, and Virginia Tech's CAD Laboratory agreed, through the assistance of Americal Technology Initiative, in 1990 to form the ACSYNT (Aircraft Synthesis) Institute. The Institute is supported by a Joint Sponsored Research Agreement to continue the research and development in computer aided conceptual design of aircraft initiated by NASA Ames Research Center and Virginia Tech's CAD Laboratory. The result of this collaboration, a feature-based, parametric computer aided aircraft conceptual design code called ACSYNT, is described. The code is based on analysis routines begun at NASA Ames in the early 1970's. ACSYNT's CAD system is based entirely on the ISO standard Programmer's Hierarchical Interactive Graphics System and is graphics-device independent. The code includes a highly interactive graphical user interface, automatically generated Hermite and B-Spline surface models, and shaded image displays. Numerous features to enhance aircraft conceptual design are described.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: AIAA PAPER 92-1268
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Improving aircraft conceptual design - A PHIGS interactive graphics interface for ACSYNT (1988)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: A CAD interface has been created for the 'ACSYNT' aircraft conceptual design code that permits the execution and control of the design process via interactive graphics menus. This CAD interface was coded entirely with the new three-dimensional graphics standard, the Programmer's Hierarchical Interactive Graphics System. The CAD/ACSYNT system is designed for use by state-of-the-art high-speed imaging work stations. Attention is given to the approaches employed in modeling, data storage, and rendering.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: AIAA PAPER 88-4481
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Infrared imaging - A validation technique for computational fluid dynamics codes used in STOVL applications (1991)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The need for a validation technique for computational fluid dynamics (CFD) codes in STOVL applications has led to research efforts to apply infrared thermal imaging techniques to visualize gaseous flow fields. Specifically, a heated, free-jet test facility was constructed. The gaseous flow field of the jet exhaust was characterized using an infrared imaging technique in the 2 to 5.6 micron wavelength band as well as conventional pitot tube and thermocouple methods. These infrared images are compared to computer-generated images using the equations of radiative exchange based on the temperature distribution in the jet exhaust measured with the thermocouple traverses. Temperature and velocity measurement techniques, infrared imaging, and the computer model of the infrared imaging technique are presented and discussed. From the study, it is concluded that infrared imaging techniques coupled with the radiative exchange equations applied to CFD models are a valid method to qualitatively verify CFD codes used in STOVL applications.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 91-0675
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    NASA TECHNICAL REPORTS
  • 5
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    Effect of buoyancy and power design parameters on hybrid airship performance (1983)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: The effects of several design parameters on the performance of hybrid airships having rotors and propellers were examined with a simple mathematical model. The parameters included buoyancy ratio, Froude number, ratio of rotor power to total power, and rotor shaft tilt. Performance variations resulting from changes in these parameters were calculated, and are presented and discussed. Performance quantities included best climb rate, equivalent vehicle L/D, and maximum speed. Performance at all speeds between hover and maximum speed was found to be sensitive to power distribution between rotors and propellers, and to rotor shaft tilt.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-1976 , Lighter-Than-Air Systems Conference; Jul 25, 1983 - Jul 27, 1983; Anaheim, CA
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    NASA TECHNICAL REPORTS
  • 6
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    Extracting dimensional geometric parameters from B-spline surface models of aircraft (1992)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Research that creates techniques to automatically obtain dimensional geometric parameters from the nonuniform B-spline surface description of an object is presented. These techniques have been implemented successfully in the aircraft design software, ACSYNT, a computer-aided design system for conceptual aircraft design created at Virginia Tech and NASA Ames. The techniques created and implemented in this research are also of significance to general-purpose design.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 92-4283 , ; 14 p.|AIAA, Aircraft Design Systems Meeting; Aug 24, 1992 - Aug 26, 1992; Hilton Head Island, SC; United States
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    NASA TECHNICAL REPORTS
  • 7
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    Control response measurements of the Skyship-500 airship (1985)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: An examination is conducted of the Skyship 500's dynamic response to control inputs from elevators, rudders, and throttles at zero, 25, and 40 kts indicated airspeed. Input frequency sweeps were made with pitch and turn controls at 25 and 40 kts, ranging in frequency from about 0.03 to 1.5 Hz. FFT data analysis was then applied to compute describing functions for each run. Frequency responses are noted to be very smooth, and comparisons between repeat runs indicate excellent agreement. Summary plots of the faired describing functions from each run form the core of the data presented. These data constitute a comprehensive and reliable data base on which to predicate future dynamic simulation mathematical models of small airship dynamic response.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 85-0881 , Lighter-Than-Air Systems Conference; Jun 26, 1985 - Jun 28, 1985; Norfolk, VA
    Format: text
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    NASA TECHNICAL REPORTS
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