Experimental study of compressible boundary layer on a cone at angles of attack-中国期刊网

摘要 Experimentalstudywasconductedforboundary-layersonasharp5°half-angleconeof400mmlengthatanglesofattack.ThemodelwastestedintheT-326hypersonicwindtunnel(ITAM)atfreestreamMachnumberM=5.95.Meanandfluctuationwallcharacteristicsoftheboundarylayeraremeasuredat0°2°3°and4°anglesofattackfordifferentstagnationpressures.PulsationmeasurementsarecarriedoutbymeansofALTPsensor.Pressureandtemperaturedistributionsalongthemodelareobtained,andtransitionbeginningandendlocationshavebeenfound.Boundarylayerstabilizationwiththeincreaseofangleofattackandthedecreaseofstagnationpressureisobserved.Highfrequencypulsationsinherenttohypersonicboundarylayer(secondmode)havebeendetected.

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Experimental study of compressible boundary layer on a cone at angles of attack

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Experimental study of compressible boundary layer on a cone at angles of attack

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