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Ice-Accretion Test Results for Three Large-Scale Swept-Wing Models in the NASA Icing Research Tunnel

机译：美国宇航局结冰研究隧道中三种大型席卷翼型的冰增冰测试结果

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Icing simulation tools and computational fluid dynamics codes are reaching levels of maturity such that they are being proposed by manufacturers for use in certification of aircraft for flight in icing conditions with increasingly less reliance on natural-icing flight testing and icing-wind-tunnel testing. Sufficient high-quality data to evaluate the performance of these tools is not currently available. The objective of this work was to generate a database of ice-accretion geometry that can be used for development and validation of icing simulation tools as well as for aerodynamic testing. Three large-scale swept wing models were built and tested at the NASA Glenn Icing Research Tunnel (IRT). The models represented the Inboard (20% semispan), Midspan (64% semispan) and Outboard stations (83% semispan) of a wing based upon a 65% scale version of the Common Research Model (CRM). The IRT models utilized a hybrid design that maintained the full-scale leading-edge geometry with a truncated afterbody and flap. The models were instrumented with surface pressure taps in order to acquire sufficient aerodynamic data to verify the hybrid model design capability to simulate the full-scale wing section. A series of ice-accretion tests were conducted over a range of total temperatures from -23.8 °C to -1.4 °C with all other conditions held constant. The results showed the changing ice-accretion morphology from rime ice at the colder temperatures to highly 3-D scallop ice in the range of-11.2 °C to -6.3 °C. Warmer temperatures generated highly 3-D ice accretion with glaze ice characteristics. The results indicated that the general scallop ice morphology was similar for all three models. Icing results were documented for limited parametric variations in angle of attack, drop size and cloud liquid-water content (LWC). The effect of velocity on ice accretion was documented for the Midspan and Outboard models for a limited number of test cases. The data suggest that there are morphological characteristics of glaze and scallop ice accretion on these swept-wing models that are dependent upon the velocity. This work has resulted in a large database of ice-accretion geometry on large-scale, swept-wing models.
机译：结冰仿真工具和计算流体动力学码达到成熟水平，使得制造商提出了用于在糖霜条件下飞行的飞行器认证的制造商，越来越依赖于自然锦绣飞行测试和冰风隧道试验。目前不可用足够的高质量数据来评估这些工具的性能。这项工作的目的是生成一个可用于开发和验证结冰仿真工具以及空气动力学测试的冰空转量几何数据库。在NASA Glenn Ching研究隧道（IRT）上建造并测试了三种大型扫翼模型。该模型基于共同研究模型（CRM）的65％级别版本，代表了机翼的内侧（20％半字），中坡（64％半峰）和舷外站（83％半字）。 IRT模型利用混合动力设计，使全尺寸的前缘几何与截短的之后的前体和襟翼保持。该模型具有表面压力抽头的仪表，以获取足够的空气动力学数据来验证混合模型设计能力，以模拟全尺寸的机翼部分。在-23.8°C至-1.4°C的一系列总温度范围内进行一系列冰增冰试验，所有其他条件保持恒定。结果表明，在较冷的温度下从霜冰的冰增冰形态变化至高度3-D扇贝冰，在-11.2°C至-6.3°C的范围内。温暖的温度产生高度3-D冰块，釉冰特性。结果表明，所有三种模型都相似的扇贝冰形态。记录了结冰的结果，用于攻角，下降尺寸和云液 - 水含量（LWC）有限的参数变化。为中坡和舷外模型记录了冰增冰的效果，用于有限数量的测试用例。这些数据表明，这些扫翼模型上存在釉料和扇贝冰的形态特征，这些扫翼模型取决于速度。这项工作导致大型扫掠翼型的大型冰渐冰几何数据库。

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