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  • Other Sources  (852)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (852)
  • 1980-1984  (852)
  • 1
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    Grob aircraft construction: The G 110 flies (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Description, specifications and test flight performance of the G 110 are provided. The G 110 completely incorporates modern GfK construction techniques which heretofore have been developed and perfected for the construction of sailplanes. The G 110 is a prototype of a GfK constructed motorized aircraft and shows much promise for the future of German aviation.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-76893 , NAS 1.15:76893
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    The solar aircraft (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A discussion is given in a popular manner of the solar powered aircraft Solair I. The achievements of the designer are detailed, and trial runs leading up to the first successful flight are given. Technical data of Solair I are listed, and brief news items about it are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-77042 , NAS 1.15:77042
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Backup flight control system for a highly maneuverable remotely piloted research vehicle (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: NASA is currently conducting flight tests of a remotely piloted subscale advanced fighter configuration as part of the Highly Maneuverable Aircraft Technology (HiMAT) program. This paper describes the initial development, user modification, and flight test experience of a back-up control system (BCS) contained within one of two onboard microprocessors. The development of the BCS proceeded in two distinct steps: the initial contractor development of control laws and logic to satisfy BCS design objectives, and user modifications required to satisfy operational requirements. A brief resume of flight qualification procedures and pilot comments is presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 80-1761 , Guidance and Control Conference; Aug 11, 1980 - Aug 13, 1980; Danvers, MA
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    NASA aeronautics R&T - A resource for aircraft design (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-08-28
    Description: This paper discusses the NASA aeronautics research and technology program from the viewpoint of the aircraft designer. The program spans the range from fundamental research to the joint validation with industry of technology for application into product development. Examples of recent developments in structures, materials, aerodynamics, controls, propulsion systems, and safety technology are presented as new additions to the designer's handbook. Finally, the major thrusts of NASA's current and planned programs which are keyed to revolutionary advances in materials science, electronics, and computer technology are addressed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 81-0925 , Annual Meeting and Technical Display on Frontiers of Achievement; May 12, 1981 - May 14, 1981; Long Beach, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    The design of sport and touring aircraft (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: General considerations concerning the design of a new aircraft are discussed, taking into account the objective to develop an aircraft can satisfy economically a certain spectrum of tasks. Requirements related to the design of sport and touring aircraft included in the past mainly a high cruising speed and short take-off and landing runs. Additional requirements for new aircraft are now low fuel consumption and optimal efficiency. A computer program for the computation of flight performance makes it possible to vary automatically a number of parameters, such as flight altitude, wing area, and wing span. The appropriate design characteristics are to a large extent determined by the selection of the flight altitude. Three different wing profiles are compared. Potential improvements with respect to the performance of the aircraft and its efficiency are related to the use of fiber composites, the employment of better propeller profiles, more efficient engines, and the utilization of suitable instrumentation for optimal flight conduction.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-77783 , NAS 1.15:77783 , DGLR-83-01 , Probl. and Develop. Trends in Gen. Aviation Symp.; Mar 24, 1983 - Mar 25, 1983; Friedrichshafen; Germany
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Installed nacelle drag-improvement tests of an M = 0.8 turboprop transport configuration (1983)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An unpowered semispan model of a representative turboprop configuration was tested to determine the effect of configuration modifications on the the nonmetric body and wing juncture. It is indicated that the jet off nacelle-installation drag can be approximately 25% of the cruise drag. However, the losses can be reduced to 17% by changes to the wing leading edge and nacelle intersection. Comparison of test results from a semispan nonmetric fuselage model with those from a full span metric fuselage show differences in angles of attack produced the same lift. It is found that the constant lift drag rise of the semispan model is higher because of the increased angle of attack to achieve the same lift.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-84302 , A-9127 , NAS 1.15:84302
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    DFVLR rotorcraft: Construction and engineering (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: A helicopter rotor test stand is described. Full scale helicopter components can be tested such as hingeless fiberglass rotors and two blade rotor with flapping hinge, or a hybrid system. The facility is used to test stability, rotor components and downwind components.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-77740 , NAS 1.15:77740
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    GROB G-112: Flight testing fulfills expectations (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The G-112 aircraft built for exhibition exhibited at the ILA '84. The G-2500 engine designed especially for this purpose is economical, requires little maintenance and generates a power of 66 kW (90 Hp). The aircraft achieves a cruising speed of 185 km/h, using a drastically reduced amount of fuel, (only 17 liters aviation fuel or premium gasoline). This small two-seater requires only a very short takeoff and taxi run of about 250 meters.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-77745 , NAS 1.15:77745
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Aerodynamic characteristics of the 40- by 80/80- by 120-foot wind tunnel at NASA Ames Research Center (1984)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The design and testing of vane sets and air-exchange inlet for the 40 x 80/80 x 120-ft wind tunnel at NASA Ames are reported. Boundary-layer analysis and 2D and 3D inviscid panel codes are employed in computer models of the system, and a 1/10-scale 2D facility and a 1/50-scale 3D model of the entire wind tunnel are used in experimental testing of the vane sets. The results are presented in graphs, photographs, drawings, and diagrams are discussed. Generally good agreement is found between the predicted and measured performance.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-85946 , A-9675 , NAS 1.15:85946
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    National Aerospace Laboratory News (Japan) (1982)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: Tests carried out in November 1981 on the stationary flap of STOL test planes at Kakuda Labs are described. Acoustic pressure, outer plate temperature of the fore flap, and acceleration, strain, and temperature of the outer plate of the main flap were measured. High load turbine inlet distortion experiments were also performed. Results of these experiments are discussed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-76962 , NAS 1.15:76962
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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