An efficient Newton-Krylov algorithm for high-fidelity aerodynamic shape optimization is used to design low-sweep wings for maximum range at transonic speeds. In this approach, the steady flow solution is obtained using the Newton method with pseudo-transient continuation. The objective function gradient is computed using the discrete-adjoint method. Linear systems from both the flow and adjoint systems are solved using a preconditioned Krylov method. A quasi-Newton optimizer is used to find the search direction. It is coupled with a line-search algorithm. Our single-point optimization results show that it is possible to design shock-free unswept wings at Mach numbers and lift coefficients comparable to the operating conditions of modern transonic transport aircraft. Robust wing designs for low-sweep and unswept wrings under the same operating conditions are obtained through multi-point optimization.
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