Last edited by Mur
Wednesday, April 22, 2020 | History

2 edition of Subsonic/transonic stall flutter investigation of a rotating rig found in the catalog.

Subsonic/transonic stall flutter investigation of a rotating rig

Subsonic/transonic stall flutter investigation of a rotating rig

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  • 23 Currently reading

Published by National Aeronautics and Space Administration, Lewis Research Center in Cleveland, Ohio .
Written in English

    Subjects:
  • Stalling (Aerodynamics),
  • Aerodynamics,
  • Aerodynamics, Transonic

  • Edition Notes

    Statementby R.R. Jutras ... [et al.]
    SeriesNASA CR -- 174625, NASA contractor report -- 174625
    ContributionsJutras, R. R, Lewis Research Center, General Electric Company. Aircraft Engine Business Group. Advanced Technology Programs Dept
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL14929429M

    The stall in accelerated flight was relatively mild, and this was attributed to the nature of the variation of lift with angle of attack for the airfoil section, the plan form of the wing, and to the fact that the initial sideslip at the stall produced (as shown by wind-tunnel tests of a model of the airplane) a more symmetrical stall.


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Subsonic/transonic stall flutter investigation of a rotating rig Download PDF EPUB FB2

Get this from a library. Subsonic/transonic stall flutter investigation of a rotating rig. [R R Jutras; Lewis Research Center.; General Electric Company. Aircraft Engine Business Group. Advanced Technology Programs Department.;]. A framework for flutter operability assessment, based upon a new set of similarity parameters, has been developed.

This set consists of four parameters which embrace both the performance characteristics in terms of corrected mass flow and corrected speed, and the flight condition in terms of inlet temperature and density (or, equivalently, inlet pressure).Cited by: 9.

PDF | A framework for flutter operability assessment, based upon a new set of similarity parameters, has been developed.

This set consists of four |. IN-FLIGHT INVESTIGATION OF A ROTATING CYLINDER-BASED STRUCTURAL EXCITATION SYSTEM FOR FLUTTER TESTING • Lura Vernon* NASA Dryden Flight Research Facility P.O. Box Edwards, California Abstract A research excitation system was test flown at the NASA Dryden Flight Research Facility on the two-seat FXL Size: 1MB.

High Angle of Attack Aerodynamics: Subsonic, Transonic, near and beyond stall. However, a comprehensive presentation of the methods and results applicable to the studies of the complex aerodynamics at high angle of attack has not been covered in monographs or textbooks.

This book is not the usual textbook in that it goes beyond just Cited by: The experimental investigation is made with a percent scale model of the Quiet Engine Program Fan C rotor system. Both subsonic/transonic (torsional mode). High-Speed Aerodynamics – Subsonic, Transonic, and Supersonic Flight.

in Physics. When an airplane is flying at subsonic speed, all of the air flowing around the airplane is at a velocity of less than the speed of sound (known as Mach 1).

Keep in mind that the air accelerates when it flows over certain parts of the airplane, like the top of. the T-tail flutter is important. Ruhlin et al. [8] conducted experimental studies of transonic T-tail flutter of a wide-body cargo/transport airplane.

They found that the transonic anti-symmetric flutter boundary for this T-tail showed an unusual sharp dip between a Mach number of and ments. The investigation also shows that shock induced separations on the fin and tailplane, the wing downwash, and the tailplane lift coefficient CLTJ may also affect ac, lap.

T At supersonic speeds, tests on Model A showed a monotonic decrease in lac, /aPI from M q to M E T 2 DETAILS OF 7XE TESTSFile Size: 3MB. Calspan’s Subsonic, Transonic Wind Tunnel is a continuous flow, variable density, closed-circuit facility with an 8 foot x 8 foot test section.

Test conditions are set via independent control of Mach number and one other pressure-dependent variable for constant Reynolds number, static pressure, dynamic pressure, or total pressure operations. with subsonic/transonic maneuver and supersonic cruise capabilities.

The model was modular in that it could be tested with a LEX, a close-coupled canard, and in an isolated wing configuration. In addition, it had provisions to mount a centerline tail and twin, wing-mounted uncanted and canted vertical tails, which were of.

There are basically three speed ranges for the flight of aircrafts, namely; subsonic, transonic and supersonic. All the three speed ranges were taken taking the speed of sound in a medium as a reference point. In this analysis, more emphasis is given to.

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SUBSONIC-TRANSONIC SUBMERGED INTAKE DESIGN FOR A CRUISE MISSILE Akman, Oral M.S., Department of Aerospace Engineering Supervisor: Assoc. Doc. Sinan Eyi November99 Pages In this thesis, aerodynamic design and optimization of subsonic-transonic submerged intake is done for specified cruise conditions.

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