As taken from the there:
The design procedure can finally be summarized as follows:
1. Solve the flow equations for ½, u1, u2, u3, p.
2. Solve the adjoint equations for à subject to appropriate boundary conditions.
3. Evaluate G and calculate the corresponding Sobolev gradient ¯ G.
4. Project ¯ G into an allowable subspace that satisfies any geometric constraints.
5. Update the shape based on the direction of steepest descent.
6. Return to 1 until convergence is reached.
And here are some constraints presented when designing:
Fixed CL.
Fixed span load distribution to present too large CL on the outboard wing which can lower the buffet margin.
Fixed wing thickness to prevent an increase in structure weight.
- Design changes can be limited to a specific spanwise range of the wing.
- Section changes can be limited to a specific chordwise range.
Smooth curvature variations via the use of Sobolev gradient.
The design procedure can finally be summarized as follows:
1. Solve the flow equations for ½, u1, u2, u3, p.
2. Solve the adjoint equations for à subject to appropriate boundary conditions.
3. Evaluate G and calculate the corresponding Sobolev gradient ¯ G.
4. Project ¯ G into an allowable subspace that satisfies any geometric constraints.
5. Update the shape based on the direction of steepest descent.
6. Return to 1 until convergence is reached.
And here are some constraints presented when designing:
Fixed CL.
Fixed span load distribution to present too large CL on the outboard wing which can lower the buffet margin.
Fixed wing thickness to prevent an increase in structure weight.
- Design changes can be limited to a specific spanwise range of the wing.
- Section changes can be limited to a specific chordwise range.
Smooth curvature variations via the use of Sobolev gradient.
This looks really great (and very detailed) ! It's amazing how much thought wing shape requires, and it applies to our own lives whether we know it or not. :O
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