Optimization and Computational Fluid Dynamics - Department of ...

5 Efficient Deterministic Approaches for Aerodynamic Shape Optimization 143
Fig. 5.17 Convergence history of design (inexact/exact drag), RAE 2822, M∞ =0.73
and α =2.0 ◦
cp
-1.5
-1
-0.5
0
0.5
1
1.5
0
0.25
Initial
Optimized (Present)
Optimized (steepest descent)
0.5
X/C
0.75 1
Fig. 5.18 Initial and optimized pressure distribution (RAE 2822, M∞ =0.73 and α =
2.0 ◦ )
drag is evaluated for the less converged state and costate variables used in
the design loop. Afterwards, on the trace of modified shapes generated during
the one-shot approach, the drag was recomputed up to an accuracy of 7
digits and compared with the inexact one. The final drag reduction after the