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  • 1
    Publication Date: 2013-08-31
    Description: An assessment of risk, in terms of delivery delays, cost overrun, and performance achievement, associated with the V/STOL technology airplane is presented. The risk is discussed in terms of weight, structure, aerodynamics, propulsion, mechanical drive, and flight controls. The analysis ensures that risks associated with the design and development of the airplane will be eliminated in the course of the program and a useful technology airplane that meets the predicted cost, schedule, and performance can be produced.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-137729 , D6-42611-ADD
    Format: application/pdf
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  • 2
    Publication Date: 2019-07-13
    Description: Results are given of several analytical studies of nacelles suitable for advanced subsonic commercial transport aircraft. The impact on the nacelle of reduced aircraft noise and increased cruise Mach number is emphasized and initially developed in terms of the individual nacelle components: inlet, fan cowl, nozzle, etc. This is achieved by relating the noise and cruise speed constraints to which the aircraft system must be designed to specific limitations on the individual nacelle components. Performance assessments are then made (separately for each nacelle component) of competitive design concepts. Overall nacelle designs, synthesized on the basis of the individual component studies, are briefly discussed.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 72-1204 , Joint Propulsion Specialist Conference; Nov. 29-Dec. 1, 1972; New Orleans, LA; US
    Format: text
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  • 3
    Publication Date: 2019-07-13
    Description: The boundary layer control (BLC) system of the quiet short-haul research airplane (QSRA) requires significant amounts of pressurized airflow for successful operation. An inlet and duct were successfully developed which removed airflow from the engine fan duct for the BLC system at or above the required total pressure of 99% of the average fan duct total pressure. The design was constrained by the tight space limitations of the QSRA nacelle. Potential flow with boundary layer analysis techniques were used as an aid to select the inlet and duct geometries. Airflow and total pressure profile data were obtained during development tests.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-141 , Aerospace Sciences Meeting; Jan. 16-18, 1978; Huntsville, AL
    Format: text
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