Flap Design Optimization for VLA by Incorporating Airworthiness Constraints
Flaps configuration has significant influence on aircraft take-off and landing performance. The flap deflection and gap are able to generate the increment in maximum lift coefficient. It indirectly influences on the take-off and landing distance and performance for given critical performance requirements. Therefore, the flap design optimization problem is formulated in which the objective function is to maximize the maximum lift coefficient (Clmax) while considering the design requirements and airworthiness constraints. The design requirement constraints are composed of takeoff and landing distance, maximum rate of climb. The airworthiness constraints such as climb gradients, ceiling altitude, rotation speed are incorporated into the flap design optimization. The design parameters are flap 2D configuration. The maximum deflection angle, gap and overlap with fixed airfoil section and chord ratio are considered as the design parameters for 2D configuration. The 2D flap analysis code is integrated into in-house Aircraft Design Synthesis Program (ADSP) implements to perform the overall aircraft performance. The optimum flap configuration is generated by implementing the optimizer solver. The optimum flap configuration is analyzed by using the CFD to validate the optimization process. Furthermore, the flap configuration will be tested by the wind tunnel. Then, the validation can be performed by using these experiment data.
Jinhwan Park Jungwon Yoon Nhu Van Nguyen Tyan Maxim Sangho Kim Jae-Woo Lee
Dept.of Aerospace Information System Engineering,Konkuk University,143-701,Seoul,Republic of Korea Dept.of R&D,Nokwon Engineering & Construction Co.,LTD.,137-130,Seoul,Republic of Korea
国际会议
黄山
英文
1-1
2012-06-18（万方平台首次上网日期，不代表论文的发表时间）