Subsonic/transonic stall flutter investigation of a rotating rig
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Subsonic/transonic stall flutter investigation of a rotating rig

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


  • Stalling (Aerodynamics),
  • Aerodynamics.,
  • Aerodynamics, Transonic.

Book details:

Edition Notes

Statementby R.R. Jutras ... [et al.].
SeriesNASA CR -- 174625., NASA contractor report -- NASA CR-174625.
ContributionsJutras, R. R., Lewis Research Center., General Electric Company. Aircraft Engine Business Group. Advanced Technology Programs Dept.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL17832281M

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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 . Sound coming from an airplane is the result of the air being disturbed as the airplane moves through it, and the resulting pressure waves that radiate out from the source of the disturbance. For a slow moving airplane, the pressure waves travel out ahead. SUBSONIC-TRANSONIC SUBMERGED INTAKE DESIGN FOR A CRUISE MISSILE Akman, Oral M.S., Department of Aerospace Engineering Supervisor: Assoc. Doc. Dr. Sinan Eyi November , 99 Pages In this thesis, aerodynamic design and optimization of subsonic-transonic submerged intake is done for specified cruise conditions. A gradient-based optimizationFile Size: 6MB.