COOLING PANEL OPTIMIZATION FOR THE ACTIVE COOLING SYSTEM OF A HYPERSONIC AIRCRAFT

Optimization of cooling panels for an active cooling system of a hyper sonic aircraft is explored, The flow passages are of rectangular cross section with one wall heated, An analytical fin-type model for incomp ressible now in smooth-wall rectangular ducts with coupled wall conduc tion is proposed. Based on this model, the minimum mass flow rate of c oolant for a single cooling panel is obtained by satisfying hydrodynam ic, thermal, and Mach number constraints, Also, the sensitivity of the optimal mass flow rate of coolant to each design variable is investig ated, In addition, numerical solutions for constant property now in re ctangular ducts, with one side rib-roughened and coupled wall conducti on, are obtained using a k-epsilon and wall function turbulence model, these results are compared with predictions of the analytical model.