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winglets

Winglet analysis on a flying wing using AeroSandbox

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TST : Problems passing the tests

A user reported via email having problems to pass the tests and use the notebooks.

Tests

============================= test session starts =============================
platform win32 -- Python 3.7.9, pytest-6.2.1, py-1.10.0, pluggy-0.13.1
rootdir: D:\Software\AeroSandbox\winglets-master, configfile: pytest.ini
plugins: dash-1.10.0
collected 16 items

tests\test_model.py ......                                               [ 37%]
tests\test_optimizer.py F.sF                                             [ 62%]
tests\test_solver.py FsFFsF                                              [100%]

================================== FAILURES ===================================
__________________________ TestOptimizer.test_put_up __________________________

self = <test_optimizer.TestOptimizer object at 0x000002D286A928C8>
optimizer = <winglets.optimizer.WingletOptimizer object at 0x000002D286AF2EC8>

    def test_put_up(self, optimizer):
    
        from winglets.optimizer import NAME_CD, NAME_CM
    
        results = optimizer.put_up()
    
        expected = {NAME_CD: 0.005628661627242771, NAME_CM: -51.54848089843833}
    
>       assert expected == results
E       AssertionError: assert {'CDi': 0.005...4848089843833} == {'CDi': 0.005...4848089843823}
E         Differing items:
E         {'CDi': 0.005628661627242771} != {'CDi': 0.005628661627242648}
E         {'Cm': -51.54848089843833} != {'Cm': -51.54848089843823}
E         Use -v to get the full diff

tests\test_optimizer.py:163: AssertionError
__________________ TestOptimizer.test_evaluate_optimal_point __________________

self = <test_optimizer.TestOptimizer object at 0x000002D286ADB848>
optimizer = <winglets.optimizer.WingletOptimizer object at 0x000002D2871A2888>

    def test_evaluate_optimal_point(self, optimizer):
    
        result = OptimizeResult(
            fun=0.9723818601228951,
            hess_inv=None,
            jac=np.array([7.32747193e-07]),
            message=b"CONVERGENCE NORM_OF_PROJECTED_GRADIENT_<=_PGTOL",
            nfev=10,
            nit=4,
            njev=5,
            status=0,
            success=True,
            x=np.array([1, 1, 1, 1, 0.85397381, 1, 1]),
        )
    
        optimizer.optimum = result
    
        targets, parameters = optimizer.evaluate_optimum()
    
        expected_targets = {"CDi": 0.005318006823391808, "Cm": -51.93177989903035}
        expected_parameters = {
            0: 0.05,
            2: 0.32,
            1: 0.65,
            3: 38,
            4: 38.42882145,
            5: 1.0,
            6: 1.0,
            "wingletAirfoil": "naca0012",
        }
    
        assert expected_parameters == parameters
>       assert expected_targets == targets
E       AssertionError: assert {'CDi': 0.005...3177989903035} == {'CDi': 0.005...3177989903027}
E         Differing items:
E         {'CDi': 0.005318006823391808} != {'CDi': 0.00531800682339165}
E         {'Cm': -51.93177989903035} != {'Cm': -51.93177989903027}
E         Use -v to get the full diff

tests\test_optimizer.py:232: AssertionError
______________________ TestFlyingWing.test_solver_alpha _______________________

self = <test_solver.TestFlyingWing object at 0x000002D28727F508>
flying_wing = <winglets.model.FlyingWing object at 0x000002D28727F348>

    def test_solver_alpha(self, flying_wing):
    
        solver = wl.WingSolver(model=flying_wing, altitude=ALTITUDE, mach=MACH)
    
        problem = solver.solve_alpha(alpha=ALPHA)
    
        results = dict(CDi=problem.CDi, CL=problem.CL, CY=problem.CY, Cm=problem.Cm)
    
        expected = {
            "CDi": 0.0007621840201544735,
            "CL": 0.17823297687249956,
            "CY": 1.8207861772476683e-18,
            "Cm": -25.046729432809073,
        }
    
>       assert expected == results
E       AssertionError: assert {'CDi': 0.000...6729432809073} == {'CDi': 0.000...4672943280919}
E         Differing items:
E         {'CDi': 0.0007621840201544735} != {'CDi': 0.0007621840201544504}
E         {'CY': 1.8207861772476683e-18} != {'CY': -3.481723488832212e-18}
E         {'CL': 0.17823297687249956} != {'CL': 0.17823297687250123}
E         {'Cm': -25.046729432809073} != {'Cm': -25.04672943280919}
E         Use -v to get the full diff

tests\test_solver.py:110: AssertionError
________________________ TestFlyingWing.test_solver_cl ________________________

self = <test_solver.TestFlyingWing object at 0x000002D287286A08>
flying_wing = <winglets.model.FlyingWing object at 0x000002D286ACC388>

    def test_solver_cl(self, flying_wing):
    
        solver = wl.WingSolver(model=flying_wing, altitude=ALTITUDE, mach=MACH)
    
        problem = solver.solve_cl(cl=CL)
    
        results = dict(CDi=problem.CDi, CL=problem.CL, CY=problem.CY, Cm=problem.Cm)
    
        expected = {
            "CDi": 0.005628661627242771,
            "CL": 0.45000738453912104,
            "CY": 2.271288523678805e-18,
            "Cm": -51.54848089843833,
        }
    
>       assert expected == results
E       AssertionError: assert {'CDi': 0.005...4848089843833} == {'CDi': 0.005...4848089843823}
E         Differing items:
E         {'CDi': 0.005628661627242771} != {'CDi': 0.005628661627242648}
E         {'CY': 2.271288523678805e-18} != {'CY': -1.6296426590460089e-18}
E         {'CL': 0.45000738453912104} != {'CL': 0.45000738453912137}
E         {'Cm': -51.54848089843833} != {'Cm': -51.54848089843823}
E         Use -v to get the full diff

tests\test_solver.py:136: AssertionError
__________________ TestFlyingWingWinglets.test_solver_alpha ___________________

self = <test_solver.TestFlyingWingWinglets object at 0x000002D286ADB608>
flying_wing_winglets = <winglets.model.FlyingWing object at 0x000002D2872896C8>

    def test_solver_alpha(self, flying_wing_winglets):
    
        solver = wl.WingSolver(model=flying_wing_winglets, altitude=ALTITUDE, mach=MACH)
    
        problem = solver.solve_alpha(alpha=ALPHA)
    
        results = dict(CDi=problem.CDi, CL=problem.CL, CY=problem.CY, Cm=problem.Cm)
    
        expected = {
            "CDi": 0.0007211988080825468,
            "CL": 0.17779760329872044,
            "CY": 1.9875634350427656e-19,
            "Cm": -24.98033280975764,
        }
    
>       assert expected == results
E       AssertionError: assert {'CDi': 0.000...8033280975764} == {'CDi': 0.000...0332809757744}
E         Differing items:
E         {'CDi': 0.0007211988080825468} != {'CDi': 0.0007211988080825262}
E         {'CY': 1.9875634350427656e-19} != {'CY': -1.1090994354044273e-18}
E         {'CL': 0.17779760329872044} != {'CL': 0.1777976032987221}
E         {'Cm': -24.98033280975764} != {'Cm': -24.980332809757744}
E         Use -v to get the full diff

tests\test_solver.py:155: AssertionError
____________________ TestFlyingWingWinglets.test_solver_cl ____________________

self = <test_solver.TestFlyingWingWinglets object at 0x000002D286ACE788>
flying_wing_winglets = <winglets.model.FlyingWing object at 0x000002D287297C48>

    def test_solver_cl(self, flying_wing_winglets):
    
        solver = wl.WingSolver(model=flying_wing_winglets, altitude=ALTITUDE, mach=MACH)
    
        problem = solver.solve_cl(cl=CL)
    
        results = dict(CDi=problem.CDi, CL=problem.CL, CY=problem.CY, Cm=problem.Cm)
    
        expected = {
            "CDi": 0.005320054099686794,
            "CL": 0.4500048433740413,
            "CY": 1.794018700567938e-18,
            "Cm": -51.88601630585104,
        }
    
        assert np.isclose(CL, results["CL"], rtol=solver.TOL_CL, atol=solver.TOL_CL)
>       assert expected == results
E       AssertionError: assert {'CDi': 0.005...8601630585104} == {'CDi': 0.005...8601630585088}
E         Differing items:
E         {'CDi': 0.005320054099686794} != {'CDi': 0.005320054099686646}
E         {'CY': 1.794018700567938e-18} != {'CY': 5.033867929681669e-19}
E         {'CL': 0.4500048433740413} != {'CL': 0.4500048433740411}
E         {'Cm': -51.88601630585104} != {'Cm': -51.88601630585088}
E         Use -v to get the full diff

tests\test_solver.py:182: AssertionError
============================== warnings summary ===============================
c:\users\lenovo\anaconda3\lib\site-packages\pyreadline\py3k_compat.py:8
  c:\users\lenovo\anaconda3\lib\site-packages\pyreadline\py3k_compat.py:8: DeprecationWarning:
  
  Using or importing the ABCs from 'collections' instead of from 'collections.abc' is deprecated since Python 3.3,and in 3.9 it will stop working

C:\Users\Lenovo\Anaconda3\lib\site-packages\win32\lib\pywintypes.py:2
  C:\Users\Lenovo\Anaconda3\lib\site-packages\win32\lib\pywintypes.py:2: DeprecationWarning:
  
  the imp module is deprecated in favour of importlib; see the module's documentation for alternative uses

-- Docs: https://docs.pytest.org/en/stable/warnings.html
=========================== short test summary info ===========================
SKIPPED [1] tests\test_optimizer.py:176: need --runslow option to run
SKIPPED [1] tests\test_solver.py:112: unconditional skip
SKIPPED [1] tests\test_solver.py:157: unconditional skip
FAILED tests/test_optimizer.py::TestOptimizer::test_put_up - AssertionError: ...
FAILED tests/test_optimizer.py::TestOptimizer::test_evaluate_optimal_point - ...
FAILED tests/test_solver.py::TestFlyingWing::test_solver_alpha - AssertionErr...
FAILED tests/test_solver.py::TestFlyingWing::test_solver_cl - AssertionError:...
FAILED tests/test_solver.py::TestFlyingWingWinglets::test_solver_alpha - Asse...
FAILED tests/test_solver.py::TestFlyingWingWinglets::test_solver_cl - Asserti...
============= 6 failed, 7 passed, 3 skipped, 2 warnings in 14.28s =============

Notebook runs

===========================================================================
Cant angle effect.ipynb
---------------------------------------------------------------------------
TypeError                                 Traceback (most recent call last)
<ipython-input-5-fbe3f15728c6> in <module>
      4 
      5 solver = wl.WingSolver(
----> 6     model=flying_wing, altitude=ALTITUDE, mach=MACH, design_cl=CL
      7 )
      8 

TypeError: __init__() got an unexpected keyword argument 'design_cl'


===========================================================================
Winglet geometry (sympy).ipynb
---------------------------------------------------------------------------
NameError                                 Traceback (most recent call last)
<ipython-input-7-79fdad8bfcfb> in <module>
----> 1 sy.simplify((final_vector.T * u_planform_vector)[0])

NameError: name 'u_planform_vector' is not defined

---------------------------------------------------------------------------
TypeError                                 Traceback (most recent call last)
<ipython-input-18-ff6c5dca814f> in <module>
      2 axes = fig.add_subplot(121, projection='3d')
      3 
----> 4 vec_1 = numerical_vector(pi/4, pi/4)
      5 vec_2 = numerical_vector(pi/4, pi/3)
      6 

TypeError: _lambdifygenerated() missing 1 required positional argument: 'delta'


===========================================================================
Global optimization.ipynb
---------------------------------------------------------------------------
 	k 	success 	iterations 	function_evaluations 	message 	J 	cd 	cm 	SPAN 	CHORD_ROOT 	TAPER_RATIO 	ANGLE_SWEEP 	ANGLE_CANT 	ANGLE_TWIST_ROOT 	ANGLE_TWIST_TIP
    0 	0.00 	False 	15 	264 	b'STOP: TOTAL NO. of ITERATIONS REACHED LIMIT' 	0.997425 	0.004427 	-51.415759 	0.02 	1.000000 	0.300000 	50.0 	80.0 	2.788998 	0.551481
    1 	0.25 	False 	15 	256 	b'STOP: TOTAL NO. of ITERATIONS REACHED LIMIT' 	0.975069 	0.004900 	-52.058265 	0.10 	0.983453 	1.000000 	50.0 	80.0 	1.783358 	1.830505
    2 	0.50 	False 	15 	168 	b'STOP: TOTAL NO. of ITERATIONS REACHED LIMIT' 	0.925946 	0.004609 	-53.249979 	0.10 	1.000000 	0.300000 	0.0 	15.0 	2.311818 	2.731971
    3 	0.75 	False 	15 	168 	b'STOP: TOTAL NO. of ITERATIONS REACHED LIMIT' 	0.872109 	0.004604 	-53.339948 	0.10 	1.000000 	0.409452 	0.0 	15.0 	2.682065 	1.773572
    4 	1.00 	False 	15 	160 	b'STOP: TOTAL NO. of ITERATIONS REACHED LIMIT' 	0.817633 	0.004602 	-53.429611 	0.10 	1.000000 	0.536835 	0.0 	15.0 	3.001250 	1.242203

---------------------------------------------------------------------------
KeyError                                  Traceback (most recent call last)
c:\users\lenovo\anaconda3\lib\site-packages\pandas\core\indexes\base.py in get_loc(self, key, method, tolerance)
   2897             try:
-> 2898                 return self._engine.get_loc(casted_key)
   2899             except KeyError as err:

pandas\_libs\index.pyx in pandas._libs.index.IndexEngine.get_loc()

pandas\_libs\index.pyx in pandas._libs.index.IndexEngine.get_loc()

pandas\_libs\hashtable_class_helper.pxi in pandas._libs.hashtable.PyObjectHashTable.get_item()

pandas\_libs\hashtable_class_helper.pxi in pandas._libs.hashtable.PyObjectHashTable.get_item()

KeyError: '$\\phi$'

The above exception was the direct cause of the following exception:

KeyError                                  Traceback (most recent call last)
<ipython-input-14-ca3b800d7406> in <module>
      3 options = dict(marker="o")
      4 
----> 5 axes[0].plot(results_df["$\\phi$"], **options)
      6 axes[0].set_ylabel("$\\phi$ [deg]")
      7 

c:\users\lenovo\anaconda3\lib\site-packages\pandas\core\frame.py in __getitem__(self, key)
   2904             if self.columns.nlevels > 1:
   2905                 return self._getitem_multilevel(key)
-> 2906             indexer = self.columns.get_loc(key)
   2907             if is_integer(indexer):
   2908                 indexer = [indexer]

c:\users\lenovo\anaconda3\lib\site-packages\pandas\core\indexes\base.py in get_loc(self, key, method, tolerance)
   2898                 return self._engine.get_loc(casted_key)
   2899             except KeyError as err:
-> 2900                 raise KeyError(key) from err
   2901 
   2902         if tolerance is not None:

KeyError: '$\\phi$'


===========================================================================
One-dimensional optimization.ipynb
---------------------------------------------------------------------------
ValueError                                Traceback (most recent call last)
<ipython-input-9-4a7b1ea43571> in <module>
     15     result = optimizer.optimize()
     16 
---> 17     cant_angle = get_optimized_cant_angle(result, initial_winglet)
     18     J = result.fun
     19     targets, parameters = optimizer.evaluate_optimum()

<ipython-input-8-346beaf4cc4a> in get_optimized_cant_angle(result, initial_winglet)
      1 def get_optimized_cant_angle(result, initial_winglet):
      2 
----> 3     return result.x.item() * initial_winglet[WingletParameters.ANGLE_CANT.value]

ValueError: can only convert an array of size 1 to a Python scalar

Check-in

Hey!

Was just curious how this project ended up working out and if you had any feedback on any unintuitive syntax, missing features, etc.!

-Peter

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