고받음각 오자이브의 비대칭 와류에 작용하는 구동기 효과 분석 = Effect of the Flow Actuator on the Asymmetric Vortex at High Angle of Attack

다국어 초록 (Multilingual Abstract)

The effect of the flow actuator on the asymmetric vortex structure around the ogive-cylinder body with fineness ratio of 4 flying at the speed of Mach 0.1 at angle of attack of 50 degree is studied. The ogive-cylinder model is developed with the actuator placed near the nose tip and numerically simulated using the in-house CFD code named KFLOW. The numerical simulation employs two different actuator modeling: one is the boundary condition given by blowing normal to the surface and another shearing on the surface. The numerical simulation reveals that response of the vortex structure to the actuation is dependent on the type of modeling as well as the strength and direction of the actuation.

참고문헌 (Reference)

1 Keener, E. R, "Side Forces on a Tangent-Ogive Forebody with a Fineness Ratio of 3.5 at High Angles of Attack and Mach Numbers from 0.1 to 0.7" NASA 1977

2 Deng, X. Y, "Recent Progress on the Study of Asymmetric Vortex Flow over Slender Bodies" 24 : 475-487, 2008

3 Bernhardt, J. E, "Proportional Control of Asymmetric Forebody Vortices" 36 (36): 2087-2093, 1998

4 E. S. Lee, "Numerical Investigation of the Behavior of the Blowing Actuator for Body Vortex Control" 2011

5 Wardlaw, A. B, "Induced Side Forces at High Angles of Attack" 13 (13): 589-593, 1976

6 Park, S. H, "Implementation of k- ω Turbulence Models in an Implicit Multigrid Method" 42 (42): 1348-1357, 2004

7 Matsuno, T, "Forebody Vortex Control on High Performance Aircraft Using PWM-Controlled Plasma Actuators" 2008

8 Poon, D, "Experimental Studies of Plasma Actuator Performance for Separation Control" AIAA 2010

9 Williams, D, "A Review of Fore Body Vortex Control Scenarios" AIAA 1997