Abstract: Focusedonthecalculationinaccuracyofexistingengineeringpredictionmethodsforwingedreentryvehicles,amodifiedcomponentpartitionstrategyandpressuremethodselectionrationaleweredeveloped.ThroughcomparisonoftheexperimentaldataandtheengineeringpredictiononlongitudeaerodynamiccharacteristicsofspaceshuttleorbiterandaX-34likevehicle,itisshownthatthepredictionmethodcanmeettheaccuracyrequirementsatMach3.0orhigher.Themaximumrelativelyerrorislessthan10%forliftcoefficientsanddragcoefficients.Comparedwiththeexistingmethods,theproposedstrategyandrationaleimprovesthepredictionaccuracyinpitchingmomentcoefficient,withthesameaccuracyinliftanddragcharacteristics.Besides,thepredictivepressuredistributionisinagreementwiththenumericalresults.

Key words: Aerodynamicforce, Engineeringpredictionmethod, Hypersonic, Supersonic, Wingedreentryvehicles