Last edited by Brazahn
Tuesday, July 28, 2020 | History

2 edition of Propulsion and airframe aerodynamic interactions of supersonic V/STOL configurations found in the catalog.

Propulsion and airframe aerodynamic interactions of supersonic V/STOL configurations

Propulsion and airframe aerodynamic interactions of supersonic V/STOL configurations

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  • 35 Currently reading

Published by National Aeronautics and Space Administration, Ames Research Center, National Technical Information Service, distributor in Moffett Field, Calif, [Springfield, Va .
Written in English

    Subjects:
  • Aerodynamics, Supersonic,
  • Vertically rising aircraft -- Jet propulsion

  • Edition Notes

    SeriesNASA contractor report -- 177343, NASA contractor report -- NASA CR-177343
    ContributionsZilz, D. E, Ames Research Center
    The Physical Object
    FormatMicroform
    Paginationv
    ID Numbers
    Open LibraryOL14982233M

      Conceptual Design of Short Takeoff Supersonic Aircraft with Cold Flow Nozzles Vignesh. M 1, Sathish. K1, Adrin Issai Arasu. L1, Dharun Lingam. K1, and Sanal Kumar. V.R 2 consumption and poor range) in turn making it unprofitable for manufacturers to produce these kinds of aircraft. It can cover a distance from India to USA in 2 ½ hours. Lighter-than-air, the first practical process for manned flight, became a reality in the 18th century but was virtually a dead-end for mass travel, but Sir George Cayley was designing gliders () and inventing engines for flight in the early realised the importance of lightweight engines and experimented with steam, petrol and even by:

    EXPERIMENTAL INVESTIGATION OF AERODYNAMIC EFFICIENCY OF MULTI WINGLETS FOR LOW SPEED OPERATIONS - Free download as Powerpoint Presentation .ppt /.pptx), PDF File .pdf), Text File .txt) or view presentation slides online. EXPERIMENTAL INVESTIGATION OF AERODYNAMIC EFFICIENCY OF MULTI WINGLETS FOR LOW SPEED OPERATIONS. Langley Research Center: Aerodynamic characteristics in pitch at a Mach number of of two variable-wing- sweep V/STOL configurations with outboard wing panels swept back 75° / (Washington, [D.C.]: National Aeronautics and Space Administration, ), also by Gerald V. Foster, Odell A. Morris, and United States National Aeronautics and.

      Abstract. The conceptual design parameters and design processes which are used to access the development of the generic stability and control method are identified and discussed in Sect. Primarily, design related commonalties and peculiarities for the range of conventional and unconventional aircraft types are : Bernd Chudoba. • The airframe noise (i.e. the noise generated by an aircraft in flight with its propulsion system noise subtracted out) program effort will be concentrated on determining the source, magnitude, and method of reducing such noise for large transport aircraft in the clean and approach (i.e., flaps and landing extended) configurations.


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Propulsion and airframe aerodynamic interactions of supersonic V/STOL configurations Download PDF EPUB FB2

Propulsion and Airframe Aerodynamic Interactions of Supersonic V/STOL Configurations Phase I: Final Report M.R. Mraz P.E. Hiley McDonnell Aircraft Company St. Louis, Missouri 1 until August - Prepared for Ames Research Center under Contract NAS September National Aeronautics and Space Administration AMES RESEARCH CENTERFile Size: 4MB.

Propulsion and airframe aerodynamic interactions of supersonic V/STOL configurations, Phase I (OCoLC) Online version: Mraz, M.R.

Propulsion and airframe aerodynamic interactions of supersonic V/STOL configurations, Phase I (OCoLC) Material Type: Government publication, National government publication: Document Type: Book. Propulsion and airframe aerodynamic interactions of supersonic V/STOL configurations, Phase I (OCoLC) Microfiche version: Mraz, M.

Propulsion and airframe aerodynamic interactions of supersonic V/STOL configurations, Phase I (OCoLC) Material Type: Document, Government publication, National government publication, Internet.

multiple V/STOL concepts (from [10]). Tilting Rotor Configurations As noted above, tiltrotor configurations have been the most successful and widely applied high speed VTOL air vehicle design. After being shown to be technically feasible with the McDonnell XV-3 and the Bell XV[15], the tiltrotor concept has now seen many thousands of hours ofFile Size: 1MB.

ASSESSMENT OF AERODYNAMIC PERFORMANCE OF V/STOL AND STOVL FIGHTER AIRCRAFT W. Nelms NASA Ames Research Center, Moffett Field, CaliforniaU.S.A.

1 SUMMARY A summary of the research efforts in the United States to assess the aerodynamic performance of V/STOL and STOVL fighter/attack aircraft is presented.

Center conducted File Size: 4MB. ergistic Airframe-Propulsion Interactions and Integrations (SnAPII). One basis for this effort can be attributed to a report by Rethorst, et al. on the elimination of induced drag [ref. Flow interactions in the region of the propulsion–airframe interface during takeoff, climb, and cruise pose a complex design problem.

Design compromises have a significant effect on the aircraft efficiency and on radiated noise. Three lift/propulsion concepts for a V/STOL supersonic combat aircraft have been compared.

The intention was to show the effect of the propulsion system on aircraft weight and size, performance, and life cycle costs for:1Vectored thrust with Plenum Chamber Burning (bypass air augmentation)2Lift engiCited by: 3.

propulsion systems. By entraining the boundary layer developing on wetted surfaces of the airframe into a propulsion system appropriately designed to compensate the airframe momentum deficit through a momentum increment, a reduction in induced over-velocities and hence propulsive power demand can be attained [5].

A systematic method for selecting the superior propulsion system for a V/STOL aircraft is presented. A relatively well-defined set of aircraft requirements and a preselected group of candidate propulsion systems form the basis for the application of the methodology.

The design and performance characCited by: 1. At the end of the workshop on breakthrough technologies described in Chapter 1 and Appendix E, the committee identified the technologies that were described in the preceding three committee then attempted to identify broad areas of technology development that could lead to breakthrough capabilities in both air and space transportation and that could potentially meet.

Full text of "NASA Technical Reports Server (NTRS) Bibliography on aerodynamics of airframe/engine integration of high-speed turbine-powered aircraft, volume 1" See other formats. @article{osti_, title = {Aerodynamic design considerations for a free-flying ducted propeller}, author = {Weir, R J}, abstractNote = {The design philosophy for a free-flying vehicle powered by a ducted propeller is presented from an aerodynamic viewpoint.

Airframe design concentrates on duct inlet lip curvature, diffuser angle, and methods of vehicle control. APA Flow Control Applications and Demonstrations I • Monday, 13 June • hrs. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA with achieving non-helicopter V/STOL capability and the search for the flying car.

Aero J Vol. Nopp, February 2. Saeed, B. and Gratton, G. Exploring the Aerodynamic Characteristics of a Blown-Annular-Wing for V/STOL Applications.

Submitted to IMechE Journal of Aerospace Engineering {Accepted}. Saeed, B. and Gratton, G. The Aerodynamic Design of Aircraft is as relevant and as forward looking today as it was in The swept wing aircraft, in becoming the mainstay of the aerospace industry, has achieved a high degree of sophistication, but much of the nuance contained in this text, required to continue advancing these designs, is lost outside a few.

The present conference discusses the comparative aerodynamic behavior of half-span and full-span delta wings, TRANAIR applications to engine/airframe integration, a zonal approach to V/STOL vehicle aerodynamics, an aerodynamic analysis of segmented aircraft configurations in high-speed flight, unstructured grid generation and FEM flow solvers, surface grid generation.

Test forward- swept wing design, advanced composites, other aerodynamic advances First forward swept wing [FSW] aircraft to fly supersonically in level flight X- This banner text can have markup.

web; books; video; audio; software; images; Toggle navigation. Gentry and Margason made lift loss measurements using a circular and a rectangular plenum chamber. The latter was designed to fit inside the fuselage of a wind tunnel model and was smaller than ideally desired.

A comparison of the loads induced on a circular plate by a single nozzle fitted to the circular and rectangular plenum chambers (Fig. 3(a)), indicated that the Cited by: 2."V/STOL Inlets and Exhaust Systems," one chapter in the Propulsion System Integration & Design Short Course Book; KU-Continuing Education, Lawrence, KS, "Compressor Aerodynamics: Two & Three Dimensional Theory," one chapter in the Aircraft Engine Analysis and Design: Practical Issues; KU-Continuing Education, Lawrence, KS The Ames Research Center (ARC), also known as NASA Ames, is a major NASA research center at Moffett Federal Airfield in California's Silicon was founded in as the second National Advisory Committee for Aeronautics (NACA) laboratory.

That agency was dissolved and its assets and personnel transferred to the newly created National Aeronautics and Space Headquarters: Mountain View, California, U.S.