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https://commonresearchmodel.larc.nasa.gov/files/2018/01/AIAA-2016-3655.pdf
(a) CAD (b) CFD Figure 2. Support system The wind tunnel model used in the ETW is a 2.7% scale model of the CRM with a wingspan of 1.586m. The model’s horizontal tailplane was set to the neutral position (0 ) and no nacelles were mounted on the wings.
http://www.aerofms.com/model_position
Being collocated with the Low Speed Wind Tunnel and providing test support in many facilities across the US gave us invaluable experience in wind tunnel operations. While providing new balances and calibrations of existing balances has been our primary supply, we have leveraged our wind tunnel experience to supply model support systems and data acquisition systems.
https://www.onera.fr/en/windtunnel/model-support
The desire to measure the component of total drag attributed to an aircraft's tail assembly, together with the continuing need for better model support corrections, has brought about the design and implementation of twin-sting support for the wind tunnel. This support system was first installed in the S2MA wind tunnel during 1993.
https://aseaero.com/wind-tunnels/
Complete Wind Tunnel Support. Our expertise covers speed regimes ranging from subsonic to hypersonic and produce test conditions for aerodynamic studies, aerothermal studies, propulsion system development, icing studies, boundary layer simulation and more.
https://apps.dtic.mil/dtic/tr/fulltext/u2/a210614.pdf
Wind Tunnel Support System Effects on a Fighter Aircraft Model at Mach Numbers from 0.6 to R,Q 12. PERSONAL AUTHOR(S) Wht tby, David G., Cal span Corporation/AEDC 0perations m 13a. TYPE Final OF REPORT 113b. I FROM TIME 8/Z3/ TO COVERED ZZ/Z/8 ''DATE OF r S PAGE uNT m 16. SUPPLEMENTARY NOTATION
https://arc.aiaa.org/doi/abs/10.2514/1.C034440
Aug 09, 2018 · [1] Cartieri A., Mouton S. and Boyet G., “ Study of Support Interference Effects at S1MA Wind Tunnel within the “SAO” Project,” 27th International Congress of the Aeronautical Sciences, ICAS Paper ICAS2010-3.11.1, Sept. 2010. Google Scholar [2] Schimanski D. and Quest J., “ Tools and Techniques for High Reynolds Number Testing Status and …Author: Andreas Waldmann, Thorsten Lutz, Ewald Krämer
https://www.powershow.com/viewht/f9a25-ZDc1Z/Wind-tunnel_techniques_powerpoint_ppt_presentation
Wind-tunnel techniques. Original wind tunnel of W.C. Kernot - 1893; 3 Wind-tunnel techniques. Two types open circuit and closed circuit; Open circuit type (fan downstream of test section) Blowing type - fan upstream of test section . test section nearly at atmospheric pressure. 4 Wind-tunnel techniques. Simulation of atmospheric boundary layer
https://apps.dtic.mil/dtic/tr/fulltext/u2/760629.pdf
low speed wind tunnels for v/stol testing by m.carbonaro survey of methods for correcring wall constrajnts in transonic wind tunnels by i.ch. vayssaire 2 interference effecrs of model support systems by e.c.carter 3 minimum required measuring times to perform instationary measurements in transonic wind tunnels
https://www.intechopen.com/books/wind-tunnels-and-experimental-fluid-dynamics-research/components-of-a-wind-tunnel-balance-design-and-calibration
2. Wind tunnel balance. The wind tunnels main function is to provide flow simulation on a model introduced in a fluid flow. Global forces and momentums on the model are mainly obtained by using different wind tunnel balances; although in special tests, local balances or pressure distribution measurement can be used as well.Cited by: 3
https://www.explainthatstuff.com/windtunnel.html
Mar 19, 2019 · This patent describes some of the problems of high-speed wind-tunnel testing and how they can be overcome. US Patent 2,711,648: Wind tunnel model support mechanism by Ralph Carlstrand, Northrop Aircraft, Inc., June 28, 1955. How do you simulate vibrations and flutter in a wind tunnel if your model is stationary?
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