Wing Design by Numerical Optimization

TLDR

The study evaluates the feasibility of computerized wing design using numerical optimization. The authors used a full‑potential inviscid aerodynamics code coupled with a conjugate‑gradient optimizer to modify wing surfaces in three test cases—reducing shock drag on a swept wing, increasing lift‑drag ratio on the same wing, and improving stall progression on a low‑speed wing—subject to volume and lift constraints. The optimization technique achieved substantial improvements in the design objectives across all three test cases, demonstrating sufficient accuracy.

Abstract

A study was conducted to assess the feasibility of performing computerized wing design by numerical optimization. The design program combined a full potential, inviscid aerodynamics code with a conjugate gradient optimization algorithm. Three design problems were selected to demonstrate the design technique. The first involved modifying the upper surface of the inboard 50% of a swept wing to reduce the shock drag subject to a constraint on wing volume. The second involved modifying the entire upper surface of the same swept wing (except the tip section) to increase the lift-drag ratio subject to constraints on wing volume and lift coefficient. The final problem involved modifying the inboard 50% of a low-speed wing to achieve good stall progression. Results from the three cases indicate that the technique is sufficiently accurate to permit substantial improvement in the design objectives.