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The boundary layer with distributed suction Sqn Ldr M R Head D S O D F C B A
An experimental investigation of the boundary layer on a porous circular cylinder
M N o 2842
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adverse pressure gradient aerodynamic aerofoil afterbody aircraft angle approximation aspect ratio body calculated chord chordwise coefﬁcient coeﬂicient constant corresponding critical Mach curves deﬁned delta wing derivatives diffusion downwash drag duct effect entry equation experimental experiments ﬁeld ﬁrst ﬁtted ﬂap ﬂat plate ﬂight formulae free-stream given increase intake integration interference drag isobars laminar boundary layer leading edge Mach number maintain laminar ﬂow maximum measured method mid-chord line Naphthalene National Physical Laboratory obtained oscillating parabolic proﬁle parameter pimple height pitot porous surface pressure distribution pressure gradient rates of suction Reynolds number rhombus shock-wave shown in Fig skin friction slot solution spanwise speed stagnation point suction ﬂow suction quantities suction velocity supersonic supervelocity Table taper tests theory total-head trailing edge tube turbulent boundary layer two-dimensional values variation velocity distribution velocity potential velocity proﬁles Wind Tunnel zero incidence