This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Novel and Inexpensive Method of Performing Dynamic Wind Tunnel Model Testing
Annotation ability available
Sector:
Language:
English
Abstract
An investigation was performed to evaluate a novel and inexpensive wind tunnel model mount for dynamic aerodynamic testing. A computer analysis code was developed to identify the dimensions of the control surface needed to produce a desired pitching motion for a delta wing. The code was then used to design and build a dynamic model apparatus that was evaluated in a low speed wind tunnel at Wichita State University. The dynamic model mount and control were evaluated for a variety of motions, including constant pitch rate ramps, constant frequency oscillations and impulse or step inputs. Results from the ramp and oscillation test indicated the system is very responsive and capable of a wide range of motion.
Authors
Topic
Citation
Mounir, I., Wayman, T., and Miller, L., "Novel and Inexpensive Method of Performing Dynamic Wind Tunnel Model Testing," SAE Technical Paper 951988, 1995, https://doi.org/10.4271/951988.Also In
References
- Lambourne, N. C. et al. “The Behavior of the Leading-Edge Vortices Over a Delta Wing Following a Sudden Change of Incidence,” NPL Aero Report 1294-ARC 81 056 1969
- Rediniotis, O. K. Klute, S. M. Telionis, D. P. “Pitching-Up Motions of Delta Wings,” AIAA Paper No 92-0278 30th Aerospace Sciences Meeting & Exhibit Reno, NV January 6-9 1992
- McCormick, B. W. Aerodynamics, Aeronautics and Flight Mechanics John Wiley & Sons New York 1984
- Mounir, I. “Aerodynamically Driven Dynamic Delta Wing Testing,” AIAA Region V Student Conference Minneapolis 1994
- Etkin, B. Dynamics of Flight - Stability and Control John Wiley & Sons New York 1982
- Hoak, D. E. USAF Stability and Control DATCOM Douglas Aircraft Company Inc. St. Louis 1960