Computation of compressible, laminar boundary layers on swept, tapered wings
| Autor: | Hans-Werner Stock, Harry P. Horton |
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| Rok vydání: | 1995 |
| Předmět: | |
| Zdroj: | Journal of Aircraft. 32:1402-1405 |
| ISSN: | 1533-3868 0021-8669 |
| Popis: | Cp = pressure coefficient, 2(p — px)/pxUl, c = chord length cfx = local skin friction coefficient for circumferential flow, 2(/jLdu/dz)w/peul f = transformed circumferential component of vector potential, i^(0, r, z)/(2£r/r0) G = transformed radial component of vector potential (alternative), (ve/qe)g g = transformed radial component of vector potential, w>2(0, r, z)/r(2gr/r0)ve H = total enthalpy Mx = Mach number of undisturbed stream, UJa p = static pressure qe = resultant external velocity, r = radial distance along generator, measured from cone apex, O r() = radius of sphere centered at O, intersecting leading edge of streamwise section S = enthalpy parameter, HIHe — 1 T = static temperature Ux = velocity of undisturbed stream (w, v, w) = velocity components in (0, r, z) directions v = spanwise velocity, — v x = arc distance around surface, r00 y = spanwise distance, r() r z = distance normal to surface y = ratio of principal specific heat capacities of gas A = transformed boundary-layer thickness 8 * = displacement thickness of circumferential flow, S'o (1 pulpeue) dz 77 = similarity variable used in present work, ue /f, p dz/V2fr/r0 VK-C = similarity variable used by Kaups and Cebeci, Vve/pe/zer0 Jg p dz 0 = polar angle in developed plane, measured from stagnation line AH A 2 = sweep angles of leading and trailing edges fji = coefficient of viscosity of gas f = transformed circumferential coordinate, So Pet*>euer() d0 p = mass density of gas o= Prandtl number of gas |
| Databáze: | OpenAIRE |
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