Bibliography: p. 15.
|Statement||by C. A. K. Irwin and P. R. Guyett.|
|Series||Aeronautical Research Council. Reports and memoranda, no. 3497, Reports and memoranda (Aeronautical Research Council (Great Britain)) ;, no. 3497.|
|Contributions||Guyett, Peter Robert, joint author.|
|LC Classifications||TL526.G7 A4 no. 3497|
|The Physical Object|
|Pagination||, 31 p.|
|Number of Pages||31|
|LC Control Number||68134014|
The Subcritical Response and Flutter of a Slender Wing Model Aircraft By D. B. PAYEN and P. R. GUYETT Structures Dept. R.A.E. Famborough Reports and Memoranda No. * September, Summary. An aeroelastic model aircraft of slender planform has been tested in a wind tunnel at low subsonic speeds. The method is applied to an aeroelastic system using its response to gust loads. Numerical results demonstrate that the method can predict the post-bifurcation regime accurately for both supercritical and subcritical flutter. Volume Subject Area: Dynamics, Vibration, and Control. Stability and Bifurcations in a Model of a Follower Loaded by: 3. The approach carried out in time and frequency domains yields the proper aerodynamic loads necessary to the study of the subcritical aeroelastic response and flutter of lifting surfaces, respectively. Physics-Based Low-Order Model for Transonic Flutter Prediction. Pure bending flutter of a swept wing in a high- density, low-speed flow A physical explanation of free play effects on the flutter response of an all movable control surface. Dale Pitt; 36th Structures, Structural Dynamics and Materials Conference August Volume 15 Cited by:
American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Irwin, C. A. K., and P. R., Guyett, “The Subcritical Response and Flutter of a Swept Wing Model,” Tech. Rept. , Aug. , Royal Aircraft Establishment, Farnborough, UK. Peters, D. A., S., Karunamoorthy, and W.-M., Cao, “ Finite State Induced-Flow Models; Part I: Two-Dimensional Thin Airfoil,” Journal of Aircraft, Vol. 32, No. 2, Mar.-Apr. , pp. – This paper presents a digital simulation method which yields the flutter speed, the flutter frequency, and the subcritical response of a system. The flutter system can be considered as a control system comprising a number of linear hysteresis elements, and the model of . The wing modal and flutter prediction of a regional aircraft wing is used as an example to verify the accuracy of the FE model with the equivalent stiffness or namely equivalent FE model. The aspect ratio of the wing is , the wing area is m 2, the sweep angle at 1/4 chord is °, and thickness ratio at wing root is
C. A. Irwin and P. R. Guyett: The Subcritical Response and Flutter of a Swept Wing Model, (Royal Aircraft Establishment, August ) Google Scholar 4. K. Isogai: On the Transonic-Dip Mechanism of Flutter of a Sweptback Wing, AIAA journal, Vol. 17, No. 7, July ) Google Scholar. Houbolt, J.C. () On identification frequencies and damping in subcritical flutter testing, NASA SP, Flutter testing techniques, A conference held at Dryden Flight Research Center, Edwards, CA, 9–10 October. Google Scholar. Multi-fractality in aeroelastic response as a precursor to flutter Journal of Sound and Vibration, Vol. A revision of the flutter margin method to predict in real-time the limit cycle oscillations onset speed with structural freeplay present in the plunge axis. The thickness of the beam of the non-tailored model (Model B) is determined so that the (theoretical) divergence point is about kPa (at M = ) which is the upper limit of the tunnel operating range, since our intention is to determine the divergence boundary of the model by the subcritical response technique [Southwell method (Sherrer.