PLA 6th generation fighter thread

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bebops

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If this guy isn't joking and is a credible source, I believe it will get revealed near US election day to send a message. Months away from now is the US election
 
by78

by78

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titled After body supersonic directional stability augmentation method for tailless configuration. Illustrations in this paper have been making the arounds for a while, so sharing the whole paper here for the record.

Abstract: Aiming at the problem of insufficient supersonic directional static stability in the tailless configuration aircraft design, an aerodynamic supersonic directional augmentation method for the after-body design is presented. Firstly, the design idea of after-body supersonic directional augmentation was made clear by the comparative analysis of the directional static stability and surface flow field between flat after-body and conventional after-body of tailless configuration. And then the influence law of the after-body shape on the supersonic directional static stability was analyzed based on the parametric configuration. Finally, the effectiveness of the after body supersonic directional stability augmentation method was verified by the comprehensive aerodynamic characteristics numerical evaluation of the typical after-body scheme. The results show that the increment of after-body lateral projected area, after-body surface spine curves and after-body surface section curves are the three most important parameters which affect the ability of after body supersonic directional augmentation. Compared to the conventional after-body, the after-body shape designed by the supersonic directional augmentation method can dramatically decrease the directional static instability of the tailless configuration at transonic and supersonic flight with drag basically unchanged.
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by78

by78

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A paper on S-inlet design for next generation fighters.

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Abstract: Thin-walled structure of advanced fighter inlet is under severe vibration and noise load due to separation of internal flow field in the S-shaped inlet, resulting in limited fatigue life of the inlet skin and the supporting structure and thus increased cost of maintenance. Therefore, the design against acoustic fatigue of the S-shaped inlet is a key challenge in the structural design of the new generation fighter. Based on an analysis of the prediction method of aerodynamic noise, the analysis method of acoustic-vibration coupling, fast finite element modeling method of inlet, and the acoustic fatigue life prediction, a design method against inlet acoustic fatigue is established. The method proposed is verified by experiments, and the experimental results are in good agreement with the analysis results.
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