446
C. Sabater
Fig. 14.8 Convergence history of the drag quantile under uncertainties and comparison with
surrogate based approach, robust optimum configuration
Fig. 14.9 Pressure coefficient for baseline and deterministic optimum configurations
14.4.9 Deterministic Results
The deterministic optimum solution (at nominal operating conditions) is found
after 106 evaluations of the objective function (CFD computations). The optimum
configuration reduces drag by 22% (31.36 drag counts), from 142.4 to 111.04
drag counts. As shown in Fig. 14.9 from the surface pressure coefficient, the new
airfoil shape replaces the normal shockwave of the upper surface by an isentropic
compression and reduces the wave drag.
C. Sabater
Fig. 14.8 Convergence history of the drag quantile under uncertainties and comparison with
surrogate based approach, robust optimum configuration
Fig. 14.9 Pressure coefficient for baseline and deterministic optimum configurations
14.4.9 Deterministic Results
The deterministic optimum solution (at nominal operating conditions) is found
after 106 evaluations of the objective function (CFD computations). The optimum
configuration reduces drag by 22% (31.36 drag counts), from 142.4 to 111.04
drag counts. As shown in Fig. 14.9 from the surface pressure coefficient, the new
airfoil shape replaces the normal shockwave of the upper surface by an isentropic
compression and reduces the wave drag.