2 edition of MAVRIC flutter model transonic limit cycle oscillation test found in the catalog.
MAVRIC flutter model transonic limit cycle oscillation test
2001 by National Aeronautics and Space Administration, Langley Research Center, Available from NASA Center for AeroSpace Information (CASI) in Hampton, Va, Hanover, MD .
Written in English
|Statement||John W. Edwards ... [et al.].|
|Series||[NASA technical memorandum] -- NASA/TM-2001-210877., NASA technical memorandum -- 210877.|
|Contributions||Edwards, John W., Langley Research Center.|
|The Physical Object|
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MAVRIC flutter model transonic limit cycle oscillation test / John W. Edwards [and four others]. Format Online Resource Book Published Hampton, Virginia: National Aeronautics and Space Administration, Langley Research Center, May Description 1 online resource (15 pages): illustrations.
URL. MAVRIC MAVRIC flutter model transonic limit cycle oscillation test book model transonic limit cycle oscillation test (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document Type: Internet Resource, Computer File: All Authors / Contributors: John W Edwards; Langley Research Center.
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Introduction. Limit cycle oscillation in aeroelastic system seems to be more prevalent in transonic air flow than in subsonic air flow according to Thomas et al. ().Certainly, LCO may be caused by structural nonlinearity no matter whether the air flow is transonic or not (Yang and Zhao, ), and the aerodynamic nonlinearity will lead to LCOs in transonic air flow even in the absence Cited by: 5.
A practical tutorial on modified condition/decision coverage. Request MAVRIC flutter model transonic limit cycle oscillation test book. Title A practical tutorial on modified condition/decision coverage [microform] / Kelly J.
Hayhurst [et al.]. Format Online MAVRIC flutter model transonic limit cycle oscillation test. Edwards JW, Schuster DM, Spain CV, Keller DF, Moses RW () MAVRIC flutter model transonic limit cycle oscillation test, AIAA p – Google Scholar Edwards JW () Transonic shock oscillations and wing flutter calculated with an interactive boundary layer coupling method, NASA TM Google ScholarCited by: 4.
The limit cycle flutter persists down to very low air densities, corresponding to altiludes ab ft, and the maximum limit-cycle-oscillation flutter amplitude does not occur at sea level.
“A Parametric Study of Transonic Airfoil Flutter and Limit Cycle Oscillation Behavior,” AIAA Paperpresented at the AIAA/ASME/ ASCE/AHS SDM Conference, Denver, CO. After the transition caused by - Δ p 0 there is a nearly sinusoidal oscillation with relatively constant amplitude i.e.
a limit cycle oscillation. The explanation of Bendiksen () is as follows: The reduction of the pressure leads to a structural wash-in effect i.e.
less bending of the swept wing is coupled with an increase of the angle of Cited by: 1. For the truss-braced wing model test, the flutter onset was preceded by a large Mach number/dynamic pressure area in which the model displayed wing/engine nacelle aeroelastic limit-cycle oscillation.
Transonic limit cycle oscillation analysis using reduced order aerodynamic models. MAVRIC flutter model transonic limit cycle oscillation test.
John Edwards, Analysis and test methods for large deployable space structures. Akira Meguro. Several examples of experimental model designs, wind tunnel tests and correlation with new theory are presented in this paper.
The goal is not only to evaluate a new theory, new computational method or new aeroelastic phonomenon, but also to provide new insights into nonlinear aeroelastic phenomena, flutter, limit cycle oscillation (LCO) and gust by: 5.
Robert J. Pegg, Summary of Flight-Test Results of the VZ-2 Tilt-Wing Aircraft, NASA TN D, Februarypp. Herman L. Bohon, Flutter of Flat Rectangular Orthotropic Panels With Biaxial Loading and Arbitrary Flow Direction, NASA TN D, September S.
Katzoff, Clarity in Technical Reporting, NASA SP, Januarypp. Feb 5 26 AIAA paper on Transport Wing Flutter Model Transonic Limit Oscillation Test 6_30_txt.
Feb 5 27 RE AIAA paper on Transport Wing Flutter Model Transonic Limit Oscillation Test 6_30_txt. Feb 5 28 RE AIAA paper on Transport Wing Flutter Model Transonic LimitOscillation Test 7_2_txt.
The data set provides excellent code validation test cases for the important class of flow conditions involving shock-induced transonic flow separation onset at low wing angles, including Limit Cycle Oscillation behavior. MAVRIC Flutter Model Transonic Limit Cycle Oscillation Test. NASA Technical Reports Server (NTRS).
Videogrammetric dynamic data were acquired at a Hz rate for time records of up to 6 seconds during portions of this flutter/Limit Cycle Oscillation (LCO) test at Mach numbers from to Spectral analysis of the deformation data is used to identify dominant frequencies in the wing motion. AEROELASTIC CONTROL (CLARK AND COX) Introduction Linear System Theory System interconnections Controllability and observability Aeroelasticity: Aerodynamic Feedback Development of a typical section model Aerodynamic model, 2D Balanced model reduction Combined aeroelastic model Development of a delta wing model Transducer eﬀects.
The aeroelastic interaction of a typical transport-aircraft structure and the transonic flow exhibits two well-known phenomena: firstly, in the “transonic dip” (Tijdeman, ) the flutter speed shows a noticeable minimum between the critical Mach number where local supersonic regions occur in the flowfield and the Mach number where massive.
The heave and pitch motions of the rigid airfoil in the flutter-test set-up are modeled by a two-degree-of-freedom system as shown in Fig. The corresponding equations of motion can be written in nondimensional form as Experiments on Heave/Pitch Limit- Cycle Oscillations Vd--b.
The Los Alamos National Laboratory/New Mexico State University filter plugging test facility: description and preliminary test results / H (online).
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