Aerodynamic optimization design of new type tandem airship based on response surface methodology
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摘要: 采用均匀试验设计的方法, 以后掠排翼式飞艇为初始气动外形, 后翼的轴、法向坐标为设计变量, 升力、阻力系数和升阻比为目标函数, 通过CFD结合响应面近似理论, 建立了气动参数的二阶响应面优化模型, 并针对排翼式飞艇的升阻特性进行了优化设计. 研究结果表明: 响应面方法是解决气动优化问题的一种行之有效的方法;优化后排翼式飞艇的气动性能得到明显改善, NACA0020, NACA0030, NACA0040排翼式飞艇的升阻比分别提高了9.61%, 6.08%, 13.08%; 飞翼的轴向和法向位置对各气动参数的影响不尽相同, 升力系数C_rm l和升阻比k对轴向位置更为敏感, 而轴向和法向位置对阻力系数C_d的影响则基本相当.
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关键词:
- 计算流体力学
Abstract: The new type tandem buoyancy-lifting airship, based onthe NACA aerofoil, not only possesses considerable volume efficiency, butalso the aerodynamic efficiency. In order to improve its aerodynamicefficiency farther, the optimum design for aerodynamic configuration oftandem airship is executed with the response surface methodology. Adoptingthe uniform experimental design method, taking the sweepback tandem airshipas the basic configuration, axis and normal coordinate of back wing as thedesign variable, lift, drag and lift-drag ratio as the objective function,the second-order response surface optimization model of aerodynamicparameter has been constructed via CFD and response surface approximationtheory. With the presented method, the optimization design is applied tolift-drag characteristic of tandem airship. The results indicate that theresponse surface methodology is effective, feasible and applicable foraerodynamic optimum design.-
Key words:
- CFD
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