A method of increasing the critical Mach number of the finite span wing by deflection of its trailing edge is provided. It is shown that the deflection of the wing’s trailing edge can increase the critical Mach number to 10 %. The possible deflection angles of the wing trailing edge depending on the Mach number were found.
critical Mach number, wing trailing edge high lift decise, angle of attack, lift coefficient, lift to drag ratio, wave drag
"Yssledovanye aэrodynamycheskykh kharakterystyk krыla konechnoho razmakha na bolshykh dozvukovыkh skorostiakh" ,
Systems of Arms and Military Equipment,