A new method for the aerodynamic design of wings with natural laminar flow is under development at the NASA Langley Research Center. The approach involves the addition of new flow constraints to an existing knowledge-based design module for use with advanced flow solvers. The uniqueness of the new approach lies in the tailoring of target pressure distributions to achieve laminar flow on transonic wings with leading-edge sweeps and Reynolds numbers typical of current transports. The method is demonstrated on the Common Research Model configuration at critical N-factor levels representative of both flight and high-Reynolds number wind tunnel turbulence levels. The design results for the flight conditions matched the target extent of laminar flow very well. The design at wind tunnel conditions raised some design issues that prompted further improvements in the method, but overall has given promising results.
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机译：NASA Langley Research Center正在开发利用自然层流的翅膀空气动力学设计的新方法。该方法涉及将新的流量约束添加到现有的基于知识的设计模块，以用于高级流量求解器。新方法的唯一性在于剪裁目标压力分布，以实现具有典型电流传输的前缘扫描和雷诺数的跨音翼的层流。在临界n因子水平上说明了该方法，其代表飞行和高雷诺数风隧道湍流水平的关键n因子水平。飞行条件的设计结果与层流的目标范围相匹配。风洞条件下的设计提出了一些设计问题，促进了该方法的进一步改进，但总体上有了有希望的结果。
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