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首页> 外文期刊>日本航空宇宙学会論文集 >小型超音速実験機全機フラッタ模型風洞試験について
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小型超音速実験機全機フラッタ模型風洞試験について

机译：所有小型超音速实验飞机的颤振模型风洞试验。

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1963年に米国で超音速旅客機（Super Sonic TranSpOrt；SST）の開発プログラム（U．S．SST program）が正式にスタートした．NASAが行った予備調査SCAT（Super-Sonic Commercial Air Transport）では-4，-15，-16，-17の4種類の機体が提案されボーイング社やロッキード社が検討した．%Three wind tunnel tests for flutter have been conducted under the development of the National Experimental Airplane for Supersonic Transport (NEXST-1) of JAXA launched in 2005. Three kinds of flutter were investigated by using three different wind tunnel models at that time. Discussion of this paper is mostly on the one for a main wing model. The planform of the NEXST-1 wing is a cranked arrow having warp in the out of plane direction. For flutter, the model showed the so called transonic dip of which bottom speed was at Mach 1.02. It was also subjected to limit cycle oscillation (LCO) in the transonic regime. The flutter was dominantly the bending of the out board wing. In the design stage of the NEXST-1, a 20% reduction was anticipated for the transonic regime by the flutter analysis with the linear aerodynamic theory. The wind tunnel experiment resulted in 21% lower in the flutter speed that was slightly higher than the assumption. The NEXST-1 aircraft was launched in the piggy back style by the solid rocket booster. Therefore, the flutter was also investigated for this launching configuration. The flutter speed reduction in this case was 27%, which was larger than that for a sole airframe. As a consequence, the design methodology for transonic flutter is thought to be confirmed for supersonic flight vehicles.
机译：1963年，在美国，超音速客机（Super Sonic TranSpOrt; SST）发展计划（U.S.SST计划）正式启动。由美国航空航天局（NASA）进行的初步调查（SCAT，超音速商业航空运输）提出了四种型号的飞机，分别为-4，-15，-16和-17，由波音和洛克希德公司进行了检查。 ％在2005年JAXA的国家超音速运输实验飞机（NEXST-1）的研制下，进行了3​​次扑扑风洞试验，当时使用三种不同的风洞模型研究了3种扑扑。 NEXST-1机翼的平面形状是在平面外弯曲的曲柄箭头，对于颤振，该模型显示了所谓的跨音速倾角，其底速在1.02马赫时，它在跨音速状态下也受到极限循环振荡（LCO）的影响，主要是外侧机翼的弯曲。在NEXST-1的设计阶段，预计将减少20％通过线性空气动力学理论通过颤振分析确定跨音速状态。风洞实验使颤振速度降低了21％，略高于假设.NEXST-1飞机在储钱罐中发射固体火箭助推器的K型飞行器，在那里还对这种发射配置的颤振进行了研究，这种情况下的颤振速度降低了27％，大于单个机身的颤振速度，因此，跨音速的设计方法认为超音速飞行器会出现颤振。

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