Theoretical calculations of the effects of finite sideslip at supersonic speeds on the span loading and rolling moment for families of thin sweptback tapered wings at an angle of attack

Thematerial givenin thisreport completes thepresentation of results obtained froma general investigation of theeffects of side slip on theaerodynamic characteristics of thinsweptback tapered wingswith sideedges psrallel to thesxisof wingsymmetry, themajorphaseof which wasreported in NACATechnical Note2@8.By meansof expressions derived therein, spsnloaddistributions havebeencalculated forseveral families of wingssideslipping at an angleof attack.Three basiccombinations of Machnumber andplanformhavebeentivestigated, eachbeingsubject to the conditions thatthe~ting tipsareparallel to theaxisofwingsymmetry andthetrailing edgeis supersonic, andto oneof thefollowing leading-" edgeconditions: (a)bothleading edgessubsonic, (b)oneleading edge subsonic andoneleading edgesupersonic, and (c)bothleading edges supersonic.In addition to theusuallimitations of linear theory andtheMachnumber restriction imposed by thesupersonic-trailing-edge condition, therestrict ionthattheMachlinefromtheleading edgeof thewingtipmaynotintersect theopposite half-wing hasbeenimposed.Therolling-moment coefficient Cz andthecorresponding stability derivative Cz havealsobeendetermined forwingswithtype(b)and (c)leading edges.Results sregivenin theformof charts whichpresent thespanload distribution forvalues of sideslip an&le up to 10°.Variations of the rolling-moment coefficient Cl withsideslip angleandof thestability derivative C2P withMachnumber arealsopresented..