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  • Other Sources  (219)
  • NASA Technical Reports  (219)
  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (219)
  • 1980-1984  (219)
  • 1984  (219)
  • 1
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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
  • 2
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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
  • 3
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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
  • 4
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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
  • 5
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    Helicopters for the future (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: Technology needed to provide the basis for creating a widening rotary wing market include: well defined and proven design; reductions in noise, vibration, and fuel consumption; improvement of flying and ride quality; better safety; reliability; maintainability; and productivity. Unsteady transonic flow, yawed flow, dynamic stall, and blade vortex interaction are some of the problems faced by scientists and engineers in the helicopter industry with rotorcraft technology seen as an important development for future advanced high speed vehicle configurations. Such aircraft as the Boeing Vertol medium lift Model 360 composite aircraft, the Sikorsky Advancing Blade Concept (ABC) aircraft, the Bell Textron XV-15 Tilt Rotor Aircraft, and the X-wing rotor aircraft are discussed in detail. Even though rotorcraft technology has become an integral part of the military scene, the potential market for its civil applications has not been fully developed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Exxon Air World; 36; 2, 19
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    F-111 natural laminar flow glove flight test data analysis and boundary layer stability analysis (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An analysis of 34 selected flight test data cases from a NASA flight program incorporating a natural laminar flow airfoil into partial wing gloves on the F-111 TACT airplane is given. This analysis determined the measured location of transition from laminar to turbulent flow. The report also contains the results of a boundary layer stability analysis of 25 of the selected cases in which the crossflow (C-F) and Tollmien-Schlichting (T-S) disturbance amplification factors are correlated with the measured transition location. The chord Reynolds numbers for these cases ranges from about 23 million to 29 million, the Mach numbers ranged from 0.80 to 0.85, and the glove leading-edge sweep angles ranged from 9 deg to 25 deg. Results indicate that the maximum extent of laminar flow varies from 56% chord to 9-deg sweep on the upper surface, and from 51% chord at 16-deg sweep to 6% chord at 25-deg sweep on the lower. The results of the boundary layer stability analysis indicate that when both C-F and T-S disturbances are amplified, an interaction takes place which reduces the maximum amplification factor of either type of disturbance that can be tolerated without causing transition.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-166051 , NAS 1.26:166051 , D6-51153
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    On-line determination of optimal flight paths for helicopters (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A procedure for computing fuel optimal fixed range trajectories is developed for helicopters. The algorithm uses a simplified dynamic model and a climb-cruise-descent assumption which simplifies the variational problem to an algebraic minimization. Development of the performance model is discussed extensively and representative results for the S-61 and S-76 helicopters are presented. The results show that the model and optimization algorithm are small enough and simple enough to be incorporated into an on-line optimization algorithm.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: American Helicopter Society, Annual Forum; May 16, 1984 - May 18, 1984; Arlington, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Performance degradation of a typical twin engine commuter type aircraft in measured natural icing conditions (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The performance of an aircraft in various measured icing conditions was investigated. Icing parameters such as liquid water content, temperature, cloud droplet sizes and distributions were measured continuously while in icing. Flight data were reduced to provide plots of the aircraft drag polars and lift curves (CL vs. alpha) for the measured ""iced'' condition as referenced to the uniced aircraft. These data were also reduced to provide plots of thrust horsepower required vs. single engine power available to show how icing affects engine out capability. It is found that performance degradation is primarily influenced by the amount and shape of the accumulated ice. Glaze icing caused the greatest aerodynamic performance penalties in terms of increased drag and reduction in lift while aerodynamic penalties due to rime icing were significantly lower.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-83564 , E-1943 , NAS 1.15:83564 , Aerospace Sci. Meeting; Jan 09, 1984 - Jan 12, 1984; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Development of flight testing techniques (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A list of students involved in research on flight analysis and development is given along with abstracts of their work. The following is a listing of the titles of each work: Longitudinal stability and control derivatives obtained from flight data of a PA-30 aircraft; Aerodynamic drag reduction tests on a box shaped vehicle; A microprocessor based anti-aliasing filter for a PCM system; Flutter prediction of a wing with active aileron control; Comparison of theoretical and flight measured local flow aerodynamics for a low aspect ratio fin; In flight thrust determination on a real time basis; A comparison of computer generated lift and drag polars for a Wortmann airfoil to flight and wind tunnel results; and Deep stall flight testing of the NASA SGS 1-36.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-176996 , NAS 1.26:176996
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Aeromechanical stability of a full-scale hingeless rotor in hover (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The aeroelastic stability in hover of a 9.8-m-diam, hingeless helicopter rotor system is evaluated. Rotor inplane damping data were obtained for rotor operation between 350 and 425 rpm for thrust coefficients between 0.0 and 0.12. At constant rotor rotational speed, a minimum inplane damping level was obtained at a thrust coefficient of approximately 0.02. At constant rotor thrust, a minimum in rotor inplane damping was measured at 400 rpm. Correlation with a comprehensive aeroelastic stability program is found to be good. The influence of different aerodynamic inflow models on predicted damping levels is shown. Best correlation with experimental data is obtained using a dynamic inflow model rather than static or quasi-static inflow models. Comparison with other full-scale, hingeless rotor stability data in hover is presented. Also, direct comparisons are made with data from a full-scale bearingless main rotor test performed on the same general-purpose test apparatus. Although the bearingless rotor is more highly damped at design tip speed and 1-g thrust operation, greater sensitivity to operating conditions is shown.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: American Helicopter Society, Annual Forum; May 16, 1984 - May 18, 1984; Arlington, VA
    Format: text
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    NASA TECHNICAL REPORTS
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