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Optimal and Robust Design of Plasma Actuator for the Control of a Cylinder Wake
Takashi Matsuno,Kentaro Ota,Takashi Kanatani,Hiromitsu Kawazoe 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
The performance of the plasma actuators for wake control and resulting drag reduction is examined and the optimization of the driving conditions of the plasma actuators were carried out by using the robust design method for wake control at high dynamic pressure conditions. The parameter design method that we used is feasible for the optimization of the control variables for flow control, under the situation that has multiple input parameters, requiring robustness, and complexity in flow phenomenon. The result of the design method gives the predicted optimal condition for reduced control parameters and that is confirmed to be robust and stable to the application test.
Unstructured-Mesh-Based Simulation for Subsonic and Supersonic Flow Control with a Plasma Actuator
Junya Yamamoto,Koji Shimoyama,Shinkyu Jeong,Shigeru Obayashi,Takashi Matsuno,Hiromitsu Kawazoe 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
A plasma actuator is a simple device that can control flow with low power supply, so this is very practical and several applications have been proposed by many researchers. In this paper, a numerical method for simulating the flow with a plasma actuator is proposed, and it is applied to supersonic flow as well as subsonic flow. This method adopts unstructured mesh so that it can be employed for complex geometries. A numerical model proposed by Suzen et al. is used for simulating the phenomena caused by a plasma actuator, and TAS-code is employed for the flow field prediction. First, this paper validated the proposed method through two test calculations for subsonic flow; the Hump model used at CFD validity workshop in NASA Langley and then the NACA0015 airfoil. According to the results of the subsonic test calculations, the present method was able to predict the effects of the plasma actuator to the flow separation correctly. Finally, a calculation with the ramp model is conducted to control the shock wave, and its capability to control the shock wave through the shift in the shock wave location was confirmed.
Low-speed Wake Analysis of Supersonic Biplane
Shuichi Ozaki,Masahito Yonezawa,Naoshi Kuratani,Toshihiro Ogawa,Shigeru Obayashi,Takashi Matsuno,Hiromitsu Kawazoe 한국항공우주학회 2008 한국항공우주학회 학술발표회 논문집 Vol.- No.-
This study was focused on the profile drag estimation from the wake survey of the now field with the wind tunnel testing. The experimental investigation was conducted with the low turbulence wind tunnel to estimate the profile drag coefficient of the supersonic biplane from the pressure loss in the wake of the model. The surveys were conducted behind the supersonic biplane model whose airfoil could realize the shock wave cancellation at design Mach number 1.7. The two-dimensional CFD simulations were also conducted to compare with the experimental results. The reduction of the test data by Jones equation gave the profile drag coefficients agreed with those obtained from the CFD simulations at zero lift conditions. However, at lifting conditions. the experimental results and the CFD results didn't agree. In this study, the profile drag characteristics of the supersonic biplane were discussed based on these results.