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  • 1
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    Full scale visualization of the wing tip vortices generated by a typical agricultural aircraft (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The trajectories of the wing tip vortices of a typical agricultural aircraft were experimentally determined by flight test. A flow visualization method, similar to the vapor screen method used in wind tunnels, was used to obtain trajectory data for a range of flight speeds, airplane configurations, and wing loadings. Detailed measurements of the spanwise surface pressure distribution were made for all test points. Further, a powered 1/8 scale model of the aircraft was designed, built, and used to obtain tip vortex trajectory data under conditions similar to that of the full scale test. The effects of light wind on the vortices were demonstrated, and the interaction of the flap vortex and the tip vortex was clearly shown in photographs and plotted trajectory data.
    Keywords: AERODYNAMICS
    Type: NASA-CR-162796 , MSSU-EIRS-ASE-80-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A method for flight-test determination of propulsive efficiency and drag (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Journal of Aircraft (ISSN 0021-8669); 22; 200-207
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    A new method for flight test determination of propulsive efficiency and drag coefficient (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A flight test method is described from which propulsive efficiency as well as parasite and induced drag coefficients can be directly determined using relatively simple instrumentation and analysis techniques. The method uses information contained in the transient response in airspeed for a small power change in level flight in addition to the usual measurement of power required for level flight. Measurements of pitch angle and longitudinal and normal acceleration are eliminated. The theoretical basis for the method, the analytical techniques used, and the results of application of the method to flight test data are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 83-2750
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Flight test evaluation of a method to determine the level flight performance of a propeller-driven aircraft (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A flight test method has been developed for determining the level flight drag and propulsive efficiency of propeller-driven aircraft. The overall drag of the aircraft is expressed in terms of the measured increment of power required to overcome a corresponding known increment of drag, which is generated by a towed drogue. The simplest form of the governing equations, D = delta D SHP/delta SHP (where D is drag and SHP is the horsepower delivered to the propeller) is such that all of the parameters on the right side of the equation can be measured in flight. An evaluation of the governing equations has been performed using data generated by flight test of a Beechcraft T-34B.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 770470 , Business Aircraft Meeting; Mar 29, 1977 - Apr 01, 1977; Wichita, KS
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Determining performance parameters of general aviation aircraft (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A method for determining propeller efficiency and drag from flight tests, using relatively simple instrumentation, is under development at Mississippi State University. Flight test data from several simple maneuvers are combined to produce sufficient information to determine the desired parameters. Information obtained from the transient response of airspeed to a step change in power or drag in level flight is utilized. Theory is developed and results of preliminary computer studies and preliminary flight test are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: In: Flight testing in the eighties; Aug 27, 1980 - Aug 29, 1980; Atlanta, GA
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Determination of cooling air mass flow for a horizontally-opposed aircraft engine installation (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The relationship between the amount of cooling air flow and the corresponding flow pressure difference across an aircraft engine was investigated in flight and on the ground. The flight test results were consistent with theory, but indicated a significant installation leakage problem. A ground test blower system was used to identify and reduce the leakage. The correlation between ground test cell determined engine orifice characteristics and flight measurements showed good agreement if the engine pressure difference was based on total pressure rather than static pressure.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 790609 , Society of Automotive Engineers, Business Aircraft Meeting and Exposition; Apr 03, 1979 - Apr 06, 1979; Wichita, KS
    Format: text
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    NASA TECHNICAL REPORTS
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