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  • 1
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    Aerodynamic performance of a 27-percent-scale AH-64 wind-tunnel model with baseline/advanced rotor blades (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Performance of a 27-percent scale model of an advanced rotor designed for the AH-64 helicopter was measured in hover and at forward speeds of 50 to 130 knots. A baseline rotor, modeled after the current AH-64 rotor, was also tested to provide data for comparison. The investigation was conducted to validate procedures used at Langley to design rotors with increased performance potential and to provide a database for evaluation of current and future rotor systems. Both rotors were operated at full-scale tip speeds. Rotor thrust, forward speed, and ground height were varied for each rotor.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Study of an advanced transport airplane design concept known as Flatbed (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design concept and configuration of the Flatbed transport aircraft are presented. The Flatbed configuration combines into one frame, the ability to haul cargo, virtually unrestrained by cross sectional dimensions of the fuselage. The feasibility and capability of the Flatbed is discussed in depth.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-159337 , LG80ER0085
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Helicopter Anti-Torque System Using Strakes (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A helicopter is disclosed with a system for controlling main-rotor torque which reduces the power and size requirements of conventional anti-torque means. The torque countering forces are generated by disrupting the main rotor downwash flowing around the fuselage. The downwash flow is separated from the fuselage surface by a strake positioned at a specified location on the fuselage. This location is determined by the particular helicopter wash pattern and fuselage configuration, generally being located between 20 deg before top dead center (TDC) and 80 deg from TDC on the fuselage side to which the main rotor blade approaches during rotation. The strake extends along the fuselage from the cabin section to the aft end and can be continuous or separated for aerodynamic surfaces such as a horizontal stabilizer.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NAS 1.71:LAR-13233-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Aerodynamic characteristics of a powered tilt-proprotor wind tunnel model (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted in the Langley V/STOL tunnel to determine the performance, stability and control, and rotor-wake interaction effects of a powered tilt-proprotor aircraft model with gimbal-hub rotors. Tests were conducted at representative flight conditions for hover, helicopter, transition, and airplane flight. Force and moment data were obtained for the complete model and for each of the two rotors. In addition to wind-speed variation, the angle of attack, angle of sideslip, rotor speed, rotor collective pitch, longitudinal cyclic pitch, rotor pylon angle, and configuration geometry were varied. The results, presented in graphical form, are available in tabular form to facilitate the validation of analytical methods of defining the aerodynamic characteristics of tilt-proprotor configurations.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-72818
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Wind tunnel investigation of a simulated gunship helicopter engine-exhaust-windstream interaction (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A wind tunnel investigation of the engine exhaust and windstream flow interaction on a gunship helicopter model was conducted in the Langley V/STOL tunnel. The investigation utilized a flow visualization technique employing neutrally buoyant helium filled bubbles to determine the cause of exhaust shield overheating during cruising flight and to evaluate means of eliminating the problem. The flow patterns were recorded with still cameras and on television magnetic tape. Exhaust flow impingement on the exhaust shield during cruise was found to cause the problem. Several flow altering devices were evaluated to find suitable ways to correct the problem. A flow deflector located on the model cowling upstream of the exhaust provides an effective solution.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-3161 , L-9923
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Wind tunnel investigation of helicopter rotor wake effects on three helicopter fuselage models (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effects of rotor downwash on helicopter fuselage aerodynamic characteristics were investigated. A rotor model for generating the downwash was mounted close to each of three fuselage models. The main report presents the force and moment data in both graphical and tabular form and the pressure data in graphical form. This supplement presents the pressure data in tabular form. Each run or parameter sweep is identified by a unique run number. The data points in each run are identified by a point number. The pressure data can be matched to the force data by matching the run and point number.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-3185-SUPPL
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    The common case study: Lockheed design of a supersonic cruise vehicle (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The objective was to compare the characteristics of SSTs designed for the same mission by Lockheed, McDonnell Douglas, British Aerospace (U.K.), Aerospatiale (France), and the USSR. This comparison was to be used to calibrate parametric design studies of the tradeoff between SST direct operating cost (DOC) and noise levels at the FAR 36 certification points. The guidelines for this common case study were to design an aircraft with the following mission: payload 23 247 kg (51 250 lbm), range - 7000 km (3780 n. mi.), and cruise Mach number - 2.2. Field length was constrained to 3505 m (11 500 ft). Other airfield constraints and fuel reserves were also specified, but no noise constraints were applied.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-158935 , LR-28705
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Rotorcraft low-speed download drag definition and its reduction (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Download drag for rotorcraft in hover and low-speed flight is a burden which significantly affects useful load, fuel, and payload. Reduction of the burden will enhance these aspects of rotorcraft and complement the forthcoming improvements in isolated rotor performance. Analyses and experimental data are available, though fragmentary, regarding gross drag, thrust recovery, and other characteristics which can be utilized to define interim rotorcraft design changes to reduce the burden. Eventually the experimental data and a comprehensive combination of rotor, rotor-wake, and potential-flow analyses can evolve to reduce the burden to an absolute minimum.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Rotorcraft parasite drag; Thirty-first Annual National Forum; May 14, 1975 - May 15, 1975; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
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