Purpose

This study aims to find the characteristics of supercritical airfoil in helicopter rotor blades for hovering phase using numerical analysis and the validation using experimental results.

Design/methodology/approach

Using numerical analysis in the forward phase of the helicopter, supercritical airfoil is compared with the conventional airfoil for the aerodynamic performance. The multiple reference frame method is used to produce the results for rotational analysis. A grid independence test was carried out, and validation was obtained using benchmark values from NASA data.

Findings

From the analysis results, a supercritical airfoil in hovering flight analysis proved that the NASA SC rotor produces 25% at 5°, 26% at 12° and 32% better thrust at 8° of collective pitch than the HH02 rotor. Helicopter performance parameters are also calculated based on momentum theory. Theoretical calculations prove that the NASA SC rotor is better than the HH02 rotor. The results of helicopter performance prove that the NASA SC rotor provides better aerodynamic efficiency than the HH02 rotor.

Originality/value

The novelty of the paper is it proved the aerodynamic performance of supercritical airfoil is performing better than the HH02 airfoil. The results are validated with the experimental values and theoretical calculations from the momentum theory.

中文翻译：

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基于超临界翼型的直升机旋翼桨叶悬停性能分析

目的

本研究旨在通过数值分析和实验结果验证来找出直升机旋翼桨叶悬停阶段超临界翼型的特性。

设计/方法论/途径

利用直升机前进阶段的数值分析，将超临界翼型与常规翼型的气动性能进行比较。多参考系方法用于生成旋转分析的结果。进行了网格独立性测试，并使用 NASA 数据的基准值进行了验证。

发现

从分析结果来看，超临界翼型悬停飞行分析证明，NASA SC 旋翼在 5° 集体螺距下产生的推力比 HH02 旋翼高 25%，在 12° 时比 HH02 旋翼高 26%，在 8° 时比 HH02 旋翼高 32%。直升机的性能参数也是基于动量理论计算的。理论计算证明NASA SC转子优于HH02转子。直升机性能结果证明NASA SC旋翼比HH02旋翼提供更好的气动效率。

原创性/价值

论文的新颖之处在于证明了超临界翼型的气动性能优于HH02翼型。结果通过动量理论的实验值和理论计算得到验证。