SSW Cruise Optimization Example #336
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* initial commit of handcrafted mesh morph * update handcrafted mesh demo * update handcrafted mesh * handcrafted mesh morphing first working demo * update handcrafted mesh code * prototype derivative test over handcrafted mesh morphing * working derivatives for the handcrafted mesh morphing * working multiproc demo of handcrafted mesh morph * demo handcrafted shape driven optimization with SSW case * update the nlbgs driver * fix plot_manager with new history file setup * update the plot manager function * update tests * add fun3d aeroelastic test interfacer * update fun3d aeroelastic test interface * update test scripts for aeroelastic test interface * update this test * move test interfaces and test utils * add new SSW tests! * update the ssw inviscid tests * update unit tests * prototype for flow state tests * add the mapbc files * fix two of the ssw tests * add bash run script for the ssw tests since there are so many * update fun3d grid interface * update fun3d grid interface * update fun3d grid interface * add debugging print statements to fun3d grid interface * update * update the test interfaces * update test * update * update * update tests * add complex step tests in ssw_tests * update complex step tests * split up real and complex ssw inviscid tests * update the ssw tests * update grid tests * update invisicd tests * remove large file * update the ssw tests folder * update teh ssw tests * add flow states + aero loads test for turb AE * add inviscid flow states, aero loads tests for flat plate * make inviscid mapbc files inviscid * add new ssw aerothermal blade stiffened exampel * update nml * add tests.sh * temporarily remove ssw_aerothermal_blade_stiffened example * update the inviscid tests * update the ssw and flat plate tests * update to plate tests * black reformat
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Multidisciplinary optimization problem for minimizing TOGW with L=W and ksfailure <= 1 on a wing with 3 different coupling optimizations: aeroelastic, aerothermal, aerothermoelastic
The same SSW flying wing geometry is used with subsonic flight
For the thermal cases, T=Tref boundary conditions are enforced at the midplane of the wing and thermal buckling constraints are enforced in each skin panel. The wing is placed in a hot flow to create the higher temperatures (not super physical but still creates a thermal design problem).
The preliminary optimizations are demonstrated using a laminar flow with a coarse BL so that the optimizations run quickly and the user can be more easily introduced to these tools.
Other items in this PR: some bug fixes for these cases and improvements to the SSW tests (for fixing derivatives of the aeroelastic on the SSW case).