格尼襟翼在冰风洞混合翼设计中的应用

doi:10.7527/S1000-6893.2018.22387

Abstract

Abstract: A project-and airworthiness-oriented hybrid-wing design criterion is presented. Based on the criterion, the Gurney flap is applied to the single hybrid-wing design in the icing tunnel test. The criterion only postulates conservative requirements for the location of stagnation point and the value of suction peak, easing the project realization and meeting airworthiness requirements. For the states deviating largely from the design point, the single hybrid-wing can still meet the criterion by adding the Gurney flap and adjusting the angle of attack, making the single hybrid-wing applicable to the icing tunnel test with a wide range of states. The use of the Gurney flap reduces the costs of designing and testing, saving time for the icing airworthiness of civil aircraft.

Key words: airworthiness-oriented, hybrid-wing design criterion, Gurney flap, location of stagnation point, value of suction peak

CLC Number:

V211.3

HAN Zhirong, ZHAO Keliang, YAN Wei. Application of Gurney flap in hybrid-wing design for icing wind tunnel[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(2): 522387-522387.

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Application of Gurney flap in hybrid-wing design for icing wind tunnel

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