By ed. Samuel Duncan Miller
This moment version of the us Air strength bibliography offers a range of books and periodical literature facing Air strength topics. It updates and expands the unique Annotated Bibliography compiled in 1971 through Carl Berger and Mary Ann Cresswell. It displays the software and recognition of the 1st bibliography not just between students yet between people with a extra basic curiosity in army aviation.
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If E is the kinetic energy of the flow at any section, we could show that: [ 1-1001 26 where E , is the kinetic energy at the nozzle. 64/Jxlb, [ 1-1011 which is essentially the same as that obtained by Albertson et al. (1950). Using his experimental results, Zijnen (1958a) studied the variation of the mixing length and the kinematic eddy viscosity and the results are shown in Fig. 1-6. From Fig. 0229, but for smaller values of X, the assumption of the constancy of the mixing length appears to be in error.
U/um = [2-64] f(t) Using the Stokes stream function: r I) = Ex2 rudr = ~ d&,f U2 0 we have urn = n / x where n = C,Uoro. Then: I) = nx 5 -/(fdt [ 2-65] Q2 0 or: I) = nx -F(t) [ 2-66] U2 E where: F ( t ) = tfdt 0 41 [ 2-67] [ 2-68] n F' We already have: u = - - x t 7 = pE- Let: E dU [2-691 [ 2-70] ar [ 2-71] = ku,b where k is a constant. Using the earlier results for urn and b , [2-711 becomes: n E = k-C2x = knC, [ 2-721 X where E is obviously independent of x . That means, the circular turbulent jet with this shear stress model has a constant eddy viscosity and hence its solution would be similar t o that of the laminar circular jet, with the difference that: r dU [ 2-731 = pknC, - ar inu or:7 = 2 X i"," :2') --- [2-741 where k = pknC,.
Since we already havep + q = 0 ; p = - 1. 6 ENTRAINMENT HYPO THESIS If Qo is the flow rate from the nozzle and if Q is the flow rate in the jet at any other x-section, it is known that the ratio &/Qo is greater than unity and increases with x. That means the jet entrains the surrounding fluid. Ricou and Spalding (1961) measured the entrainment in circular jets directly, using a rather simple device. We could write: Q = [2-371 2nrdru 0 ?!! , close to zero) and ve is the entrainment velocity. Once again, we have obtained the second equation.
An Aerospace Bibliography by ed. Samuel Duncan Miller