Analysis of the effect of surface heating on boundary layer development over an NLS-0215 airfoil

Abstract

Flows over a NU-0215 airfoil with and without flush mounted surface heating were analyzed with a two dimensional fourth order boundary layer code. Constant wall temperature and decreasing wall temperature heating cases were studied for different surface heating lengths. Boundary layer properties: tangential velocity, normal velocity, vorticity, transition location and separation location were presented for these temperature distributions. Modified boundary layer properties, due to heating are shown to persist well after heating is stopped, even when the flow is turbulent. These boundary layer results also indicate that with the proper selection of surface temperature variation and length transition can be delayed. C, = P = '-0 R = Re = Re, = S = tj = T = u = v = 9 = Nomenclature pressure coefficient pressure body radius radial coordinate Reynolds number vorticity Reynolds number tangential coordinate transverse curvature term static temperature tangential component of velocity normal component of velocity stretched y-coordinate Y = normal coordinate Z = axial body coordinate i = vorticity/Ue q = non-dimensional normal coordinate p = molecular viscosity < = transformed tangential coordinate p = density