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Wednesday, October 21, 2020 | History

2 edition of Experimental results of a deflected thrust V/STOL nozzle research program found in the catalog.

Experimental results of a deflected thrust V/STOL nozzle research program

Paul L. Burstadt

Experimental results of a deflected thrust V/STOL nozzle research program

by Paul L. Burstadt

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Published by NASA, For sale by the National Technical Information Service in [Washington, D.C.], [Springfield, Va .
Written in English

    Subjects:
  • Jet nozzles.,
  • Coriolis force.

  • Edition Notes

    StatementPaul L. Burstadt and Albert L. Johns ; prepared for the Twenty-First Aerospace Sciences Conference, sponsored by the American Institute of Aeronautics, Reno, Nevada, January 10-13, 1983.
    SeriesNASA technical memorandum -- 83069.
    ContributionsJohns, Albert L., American Institute of Aeronautics and Astronautics., Lewis Research Center., AIAA Aerospace Sciences Meeting (21st : 1983 : Reno, Nev.)
    The Physical Object
    Pagination24 p. :
    Number of Pages24
    ID Numbers
    Open LibraryOL17800304M

    G.V.R. Rao method, Exhaust Nozzle Contour for Optimization thrust, jet propulsion, June, The problem of high-speed compressible flow through focused round shape nozzles is studied computationally mistreatment the final purpose ANSYS Fluent. A pressure-based coupled solver formulation with weighted second-order central-File Size: 1MB. thrust vectoring was achieved by reducing flow area left of the nozzle centerline and increasing flow area right of the nozzle centerline; a skewed throat deflected the flow in the lateral direction. The peak thrust efficiency of the unvectored nozzle was approximately 1 to 2 percent lower than that of most high-performance exhaust nozzles.

    NASA TN D, Goodson, K. W.: Aerodynamic Characteristics of Wind Tunnel Model Compared With Flight Test Craft for Four-Propel 1 er Tilt-Wing V/STOL Aircraft XC Presented at the Ames Research Center Conference on V/STOL and STOL . The McDonnell Douglas F STOL/MTD is a modified F Eagle. Developed as a technology demonstrator, the F STOL/MTD carried out research for studying the effects of thrust vectoring and enhanced maneuverability. The aircraft used for the project was pre-production TFA No. 1, the first two-seat F Eagle built by McDonnell Douglas, the sixth F off the assembly line, and was the Manufacturer: McDonnell Douglas.

    A different British VTOL project was the gyrodyne, where a rotor is powered during take-off and landing but which then freewheels during flight, with separate propulsion engines providing forward ng with the Fairey Gyrodyne, this type of aircraft later evolved into the much larger twin-engined Fairey Rotodyne, that used tipjets to power the rotor on take-off and landing but which.   With this software you can investigate how a turbojet or rocket nozzle produces thrust by changing the values of different factors that affect thrust. By changing the shape of the nozzle and the flow conditions upstream and downstream, you can control both the amount of gas that passes through the nozzle and the exit velocity.. There is another version of this program that has been modified.


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Experimental results of a deflected thrust V/STOL nozzle research program by Paul L. Burstadt Download PDF EPUB FB2

Get this from a library. Experimental results of a deflected thrust V/STOL nozzle research program. [Paul L Burstadt; Albert L Johns; American Institute of Aeronautics and Astronautics.; Lewis Research. Four deflected thrust nozzle concepts, designed to operate at the low pressure ratio typical of high bypass-ratio turbofan engines for medium speed (subsonic) V/STOL aircraft, were studied.

Maps of overall performance characteristics and exit velocity distributions are used to highlight similarities and differences between the four concepts. The results again consist of the nozzle thrust coefficient and thrust vector angle versus the nozzle specific corrected airflow.

thrust coefficient showed a slight drop as a result of extending the flap, however, the thrust deflecting angle increased significantly from 60'.

to 76'.File Size: 4MB. Analytically determined secondary flows at the exit of a 90 deg circular pipe bend are compared with the experimental results from the more complex three dimensional geometries.

The relative impact of total-pressure losses and secondary flows on nozzle thrust coefficient is addressed by numerical integration of exit velocity measurementsAuthor: P. Burstadt and A. Johns. Analytically determined secondary flows at the exit of a 90 deg circular pipe bend are compared with the experimental results from the more complex three dimensional geometries.

The relative impact of total-pressure losses and secondary flows on nozzle thrust coefficient is addressed by numerical integration of exit velocity : A. Johns and P. Burstadt.

Results are presented for 3n experimental study of four deflected thrust nozzle concepts, designed to operate 3t the low pressure ratio typical of high bypass-ratio turbofan engines for medium speed (subsonic) V/STOL aircraft.

Experimental results of a deflected thrust V/STOL nozzle research program: Exploring in aerospace rocketry: an introduction to the fundamentals of rocketry developed at the NASA Lewis Research Center, Cleveland, Ohio: FAA-EE: Gaseous-helium requirements for the discharge of liquid hydrogen from a meter- (ft-) diameter spherical tank.

Close Drawer Menu Close Drawer Menu Menu. Home; Journals. AIAA Journal; Journal of Aerospace Information Systems; Journal of Air Transportation; Journal of Aircraft; Journal of. (STOL) transport aircraft with various types of powered lift systems (PLS), performed at the Central Aerohydrodynamic Institute (TsAGI), named after Prof.

N.E. Zhukovsky. The test results obtained in the TsAGI Т large wind tunnel correspond to the experimental aircraft "Photon" with wing jet. The architecture fits with electric propulsion and subsonic aircrafts (Mach ). In particular, it has verified that the deflection angle of the jet (and of the thrust) is a function of both.

Thrust and jet directional control using the Coanda effect. To validate these results, experimental investigations are required on a non-swept nozzle thrust vectoring efficiency is An experimental investigation was carried out of the development of steady, laminar, incompressible flow of a Newtonian fluid in the entry region of a curved pipe for the entry condition of uniform by: Nozzle effects on thrust and inlet pressure of a multi-cycle air-breathing pulse detonation engine (APDE) are investigated experimentally.

An APDE with 68 mm in diameter and 2 mm in length is operated using gasoline/air mixture. Straight nozzle, converging nozzle, converging-diverging nozzle and diverging nozzle are by: Hole-Type Aerospike Compound Nozzle Thrust Vectoring Stanley Ikuo Beebe Compound aerospike nozzles were designed and tested as part of an ongoing experimental study to determine the feasibility of thrust vectoring an aerospike nozzle with the addition of a File Size: 2MB.

Development of Thrust Deflection and Vectoring - V/STOL The progress with the use of deflected thrust in European V/STOL airplanes is reviewed. The difficulties which arise in adopting this concept are examined and commented upon in the light of Cited by: 1.

In my previous blogs I discussed the early experimental, prototype and operational V/STOL combat jet aircraft that were developed in the late ’s through to the late ’s. By the ’s significant improvements had been made in performance, handling and the weapons load capability of new V/STOL combat following is a brief history on these second generation V/STOL.

Research on the coupled design method for the aerodynamic configuration of a mixed flow exhaust system with a confluent mixer. Experimental Study of TICTOP Nozzles. 3 April Design of an arc-based thrust-optimized nozzle by: for V/STOL safety Ref.

1, for improved the STOL of is require-the lift STOL corresponding interesting achieving "ultrashort" and the STOL practical word ultrashort the 50 ft of being less, become be competitive that STOL toward ultrashort they from V/STOL. on the augmentor-wing three to ultra-STOL the concept, research program.

CONCEPT File Size: 8MB. nozzles boeing weapons squadron thrust marine development cockpit roth collection landing bae harrier equipped stol pilot mick roth collection Whether you've loved the book or not, if you give your honest and detailed thoughts then people will find new books that are right for them.

Pitch thrust vectoring was implemented by blocking the nozzle exit and deflecting a door in the lower nozzle flap. The test nozzle pressure ratio was varied up todepending on model geometry.

Results indicate that both pitch vectoring concepts produced resultant pitch vector angles which were nearly equal to the geometric pitch deflection. a prediction code for the thrust performance of two-dimensional, non-axisynnetric, converging diverging nozzles thesis angela m.

geatz afit/gae/eny/File Size: KB.An Experiment on Aerodynamic Nozzles at M= 2 By J. REID COMMUNICATED BY THE DEPUTY CONTROLLER AIRCRAFT (RESEARCH AND DEVELOPMENT), MINISTRY OF AVIATION Reports and Memoranda No. * November, I Summary. In an aerodynamic nozzle a convergent primary nozzle is housed within an afterbody which is surrounded.The V/STOL program also led to the development of two new flight simulators that were used extensively in conjunction with Ames V/STOL flight research.

From his position as division chief, Bill Harper encouraged the development of the Six-Degree-of-Freedom hover flight simulator (fig. ), the first large motion device at Ames.