Aerodynamics

aerodynamic centre aerofoil aileron aircraft altitude angle aspect ratio axis Bernoulli's Theorem boundary layer C₁ camber centre of gravity centre of pressure chord circulation climb components compressibility condition Consider constant curve cylinder defined deflection denoted density depicted in Fig downwash drag coefficient dynamic effect elevator equation equivalent airspeed flap flow past fluid force form drag free stream given gives illustrated in Fig incidence increase increment induced drag laminar leading edge leading edge slot lift coefficient lower surface M₁ Mach number maximum minimum drag obtained P₁ parameters pitching pitching moment positive PV2S reduced region Reynolds number shock wave shown in Fig skin friction stagnation point straight and level stream function streamline subsonic tail trailing edge tube tunnel turbulent two-dimensional upper surface velocity viscous vortex vorticity zero ди ду дх