Remote and Feedback Control of the Flap Angle in a Wind Tunnel Test Model by Optical Measurement

We have developed a remote and precise feedback control system using optical measurement technology to alter the angle of a flap, which is part of a wind tunnel test model, automatically and to earn the aerodynamic data efficiently. To rectify the wasteful circumstance that Japan Aerospace Exploration Agency (JAXA)’s low-turbulence wind tunnel stops ventilation every time to switch model configurations, we repaired hardware for remote operation and generated software for feedback control. As a result, we have accomplished a system that dramatically advances the efficiency of wind tunnel tests. Moreover, the system was able to consider the deformation of the model through optical measurement; the system controlled flap angles with errors less than the minimum resolution of optical measurement equipment. Consequently, we successfully grasped the nonlinearity of three aerodynamic coefficients C L , C D , and C M p that was impossible so far.

[1]  C. P. van Dam,et al.  The aerodynamic design of multi-element high-lift systems for transport airplanes , 2002 .

[2]  Andreas-René Hübner,et al.  Integrated Experimental and Numerical Research on the Aerodynamics of Unsteady Moving Aircraft , 2007 .

[3]  Shigeya Watanabe,et al.  Stereoscopic PIV measurements of leading edge separation vortices on a cranked arrow wing , 2004 .

[4]  K. Asai,et al.  A review of pressure-sensitive paint for high-speed and unsteady aerodynamics , 2008 .

[5]  Dimitri J. Mavriplis,et al.  Progress in CFD Discretizations, Algorithms and Solvers for Aerodynamic Flows , 2019, AIAA Aviation 2019 Forum.

[6]  Christopher L. Rumsey,et al.  Overview and Summary of the Second AIAA High-Lift Prediction Workshop , 2015 .

[7]  Shunsuke Koike,et al.  Time-Resolved Stereoscopic PIV Measurement of Unsteady Wingtip Flowfield , 2012 .

[8]  K. Nakakita,et al.  Simultaneous visualization of transonic buffet on a rocket faring model using unsteady PSP measurement and Schlieren method , 2017, International Congress on High-Speed Imaging and Photonics.

[9]  A. Bergmann.  Modern Wind Tunnel Techniques for Unsteady Testing – Development of Dynamic Test Rigs , 2009 .

[10]  Kazunori Mitsuo,et al.  Practical pressure-sensitive paint measurement system for industrial wind tunnels at JAXA , 2006 .

[11]  Ichiro Okura,et al.  Novel Pressure-Sensitive Paint for Cryogenic and Unsteady Wind-Tunnel Testing , 2002 .

[12]  R. Adrian.  Particle-Imaging Techniques for Experimental Fluid Mechanics , 1991 .

[13]  Nigel J. Taylor,et al.  Progress in Geometry Modeling and Mesh Generation Toward the CFD Vision 2030 , 2019, AIAA Aviation 2019 Forum.

[14]  J. Bell,et al.  Pressure-sensitive paint in aerodynamic testing , 1993 .

[15]  C. L. Rumsey,et al.  Summary of the First AIAA CFD High Lift Prediction Workshop (invited) , 2011 .