襟翼表面粗糙度对多段翼型升力的影响

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1、第6卷第1期航空工程进展V01．6No．12015年2月ADVANCESINAERONAUTICALSCIENCEANDENGINEERINGFeb．2015文章编号：1674—8190(2015)01—093—06襟翼表面粗糙度对多段翼型升力的影响朱奇亮，高永卫，叶正寅(西北工业大学翼型叶栅空气动力学国防科技重点实验室，两安710072)摘要：在襟翼上表面填充多孔吸声材料，虽然缝道的噪声有所降低，但翼型升力系数也有较大损失。为了确定是否因多孑L材料造成翼面粗糙度增加而降低了升力系数，也为了进一步确定数值模拟中粗糙表面简化模型的适用性·通过风洞试验和数值模拟进行研究。数值模拟采用沿流

2、向三角形凸起模拟吸声材料的粗糙度，采用ANSYS-Fluent的二维模块、非结构网格和}。SST湍流模型进行计算。风洞试验在某NF一3低速翼型风洞中完成，采用等弦长的二维测压模型，光滑模型表面是通过在吸声材料上覆盖光滑薄膜实现的。结果表明：可以采用沿流向三角形凸起模拟吸声材料的粗糙度对升力特性的影响；吸声材料的粗糙度影响翼型的升力系数。因此，若通过吸声材料降低缝道流动噪声，需要进一步研究吸声性能好且表面比较光滑的材料／结构。关键词：风洞试验；吸声材料；粗糙度；多段翼型；三角形凸起模型中图分类号：V21】．7文献标识码：AInfluenceofFlapSurfaceRoughnesso

3、ntheLiftofMulti·elementAirfoilZhuQiliang，GaoYongwei，YeZhengyin(NationalKeyLaboratoryofScienceandTechnologyonAerodynamicDesignandResearch，NorthwesternPolyteehnicalUniversity，Xi’an710072，China)Abstract：Theuppersurfaceofflapisfilledwithporoussound—absorbingmaterial．Thewindtunnelexperimentisaccompl

4、ishedinNF一3low—speedwindtunnel．Theresultshowsthat，althoughthenoiseofgapisdecreased，theairfoilliftcoefficientisofalargerloss．InordertOdeterminewhethertheincreasedroughnessofflapsurfacebyporousmaterialcausesthedropofliftcoefficient，anddeterminetheapplicabilityofnumericalsimulatedtheroughsurfacewi

5、thasimplifiedmodel，theexperimentandnumericalsimulationresearcharebothapplied．Thetriangularprotrusionalongtheflowdirectionisusedtosimulatetheroughnessofabsorptionmaterial．Thean—mericalsimulationiscarriedonthetwodimensionalsimulationofANSYSFluentwiththeunstructuredmeshandk-wSSTturbulencemodel．The

6、experimentmodelistwo—dimensionalmodelwiththesamechordletlgth．Thesmoothandroughsituationsareachievedbyfillingsound—absorbingporousmaterialinuppersurfaceofflapandusingplasticmembranetOoverlapitornot．Theresultshowsthatthetriangularprotrusioncansimulatetheroughnessofabsorptionmaterialandtheroughnes

7、sofsound—．absorbingmaterialindeedaffectairfoilliftcoeffi—．cient．Thus，furtherresearchonsmoothsurfaceofsound—absorbingmateriaI／structureisneededbeforeusingthesound—absorbingmaterialtOreducetheflownoiseingap．Keywords：windtunnelexperi