Updated naming to use Airfoil2D and Airfoil3D

Code should work better now

Author: pjuangph

2D_design.md

@@ -10,7 +10,7 @@ import numpy as np
 from pyturbo.aero import *
 from pyturbo.helper import *
 
-stator_hub = airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58) # This creates the camberline
+stator_hub = Airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58) # This creates the camberline
 stator_hub.le_thickness_add(0.04)
 ps_height = [0.0500,0.0200,-0.0100]
 ps_height_loc = exp_ratio(1.2,len(ps_height)+2,0.95)

3D_design.md

@@ -15,7 +15,7 @@ The code below shows an example of how to build a 3D Blade from 2D designs locat
 
 ```
 # Hub Geometry
-stator_hub = airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
+stator_hub = Airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
 stator_hub.le_thickness_add(0.04)
 ps_height = [0.0500,0.0200,-0.0100]
 ps_height = [0.0500,0.0200,-0.0100]
@@ -29,7 +29,7 @@ stator_hub.le_thickness_match()
 stator_hub.flow_guidance2(10)
 
 # Tip Geometry
-stator_tip = airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
+stator_tip = Airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
 stator_tip.le_thickness_add(0.04)
 ps_height = [0.0500,0.0200,-0.0100]
 ps_height_loc = exp_ratio(1.2,len(ps_height)+2,0.95)

pyproject.toml

@@ -1,6 +1,6 @@
 [tool.poetry]
 name = "pyturbo-aero"
-version = "1.0.14"
+version = "1.0.16"
 description = "PyTurbo_Aero is a Turbomachinery blade design library that lets you create a full 3D blades and passages."
 authors = ["Paht Juangphanich <[email protected]>"]
 packages = [

pyturbo/aero/airfoil3D.py

@@ -18,7 +18,7 @@
 
 
 class stack_type(enum.Enum):
-    """class defining the type of stacking for airfoil2D profiles
+    """class defining the type of stacking for Airfoil2D profiles
 
     Args:
         enum (enum.Emum): inherits enum
@@ -33,7 +33,7 @@ class Airfoil3D():
     '''
         Properties
     '''
-    profileArray: List[airfoil2D]
+    profileArray: List[Airfoil2D]
     profileSpan: List[float] 
     span:float 
     IsSplineFitted: bool
@@ -121,12 +121,12 @@ class Airfoil3D():
 
     """Defines a 3D Airfoil to be used in a channel
     """
-    def __init__(self, profileArray: List[airfoil2D], profile_loc: List[float], height: float):
+    def __init__(self, profileArray: List[Airfoil2D], profile_loc: List[float], height: float):
         """Constructs a 3D Airfoil
 
         Args:
-            profileArray (List[airfoil2D]): array of airfoil2D profiles
-            profile_loc (List[float]): location of the airfoil2D profiles
+            profileArray (List[Airfoil2D]): array of Airfoil2D profiles
+            profile_loc (List[float]): location of the Airfoil2D profiles
             height (float): height of the 3D blade
         """
         self.profileArray = profileArray

pyturbo/aero/airfoil_wavy.py

@@ -5,14 +5,14 @@
 from ..helper import derivative_1, bezier,cosd,sind
 import math
 
-class airfoil_wavy(airfoil3D):
+class airfoil_wavy(Airfoil3D):
     """Makes the surface of the airfoil: LE, TE, SS, PS wavy
     """
     def __init__(self,profileArray,profile_loc,height):
-        """Initializes a wavy airfoil from an array of profiles, location and height, same as airfoil3D
+        """Initializes a wavy airfoil from an array of profiles, location and height, same as Airfoil3D
 
         Args:
-            profileArray ([airfoil2D]): Array of 2D airfoil profiles 
+            profileArray ([Airfoil2D]): Array of 2D airfoil profiles 
             profile_loc ([List[float]]): Locations in terms of percent span where these 2D airfoils are located 
             height ([float]): height of the airfoil
         """

tests/aero_design_test.py

@@ -2,14 +2,15 @@
 import sys, copy
 sys.path.insert(0, "../../")
 import numpy as np
-from pyturbo.aero import airfoil2D,airfoil3D,airfoil_wavy,stack_type, passage2D
+from pyturbo.aero import Airfoil2D,Airfoil3D,airfoil_wavy,stack_type, passage2D
 from pyturbo.helper import *
 import matplotlib.pyplot as plt
 from math import pi
+import math 
 
 class TestDesign(unittest.TestCase):
     def test_2D_stator(self):
-        # stator_hub = airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
+        # stator_hub = Airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
 
         # stator_hub.le_thickness_add(0.08)
         # ps_height = [0.0500,0.0200,-0.0100]
@@ -32,7 +33,7 @@ def test_2D_stator(self):
         pass
 
     def test_2D_rotor(self):
-        # rotor_hub = airfoil2D(alpha1=40,alpha2=60,axial_chord=5.119,stagger=20)
+        # rotor_hub = Airfoil2D(alpha1=40,alpha2=60,axial_chord=5.119,stagger=20)
 
         # rotor_hub.le_thickness_add(0.08)
         # ps_height = [-0.0500,-0.0200,-0.0100]
@@ -50,7 +51,7 @@ def test_2D_rotor(self):
 
     def test_3D_Stator(self):
         # Hub Geometry
-        # stator_hub = airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
+        # stator_hub = Airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
         # stator_hub.le_thickness_add(0.04)
         # ps_height = [0.0500,0.0200,-0.0100]
         # ps_height = [0.0500,0.0200,-0.0100]
@@ -64,7 +65,7 @@ def test_3D_Stator(self):
         # stator_hub.flow_guidance2(10)
 
         # # Tip Geometry
-        # stator_tip = airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
+        # stator_tip = Airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
         # stator_tip.le_thickness_add(0.04)
         # ps_height = [0.0500,0.0200,-0.0100]
         # ps_height_loc = exp_ratio(1.2,len(ps_height)+2,0.95)
@@ -80,7 +81,7 @@ def test_3D_Stator(self):
         # plt.clf()
         # plt.close('all')
         # # Begin 3D design
-        # stator3D = airfoil3D([stator_hub,stator_tip],[0,1],0.05)
+        # stator3D = Airfoil3D([stator_hub,stator_tip],[0,1],0.05)
         # stator3D.stack(stack_type.centroid)
         # # stator3D.lean_add([0, 0.05, 1], [0,0.5,1])
         # stator3D.create_blade(100,80,20)
@@ -93,7 +94,7 @@ def test_stator3D_wavy_const_te(self):
             Wavy with constant trailing edge
         '''
         # # Hub Geometry
-        # stator_hub = airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
+        # stator_hub = Airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
         # stator_hub.le_thickness_add(0.04)
         # ps_height = [0.0500,0.0200,-0.0100]
         # stator_hub.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2) 
@@ -107,7 +108,7 @@ def test_stator3D_wavy_const_te(self):
         # # stator_hub.plot2D()
 
         # # Tip Geometry
-        # stator_tip = airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
+        # stator_tip = Airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
         # stator_tip.le_thickness_add(0.04)
         # ps_height = [0.0500,0.0200,-0.0100]
         # stator_tip.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2)
@@ -121,7 +122,7 @@ def test_stator3D_wavy_const_te(self):
 
         # # Begin 3D design
         # span = 0.05
-        # stator3D = airfoil3D([stator_hub,stator_tip],[0,1],0.05)
+        # stator3D = Airfoil3D([stator_hub,stator_tip],[0,1],0.05)
         # stator3D.stack(stack_type.trailing_edge)
         # stator3D.lean_add([0, 0.05, 0], [0,0.5,1])
         # stator3D.create_blade(100,100,20)
@@ -155,7 +156,7 @@ def test_wavy(self):
             Wavy without constant trailing edge
         '''
         # # Hub Geometry
-        # stator_hub = airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
+        # stator_hub = Airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
         # stator_hub.le_thickness_add(0.04)
         # ps_height = [0.0500,0.0200,-0.0100]
         # stator_hub.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2) 
@@ -169,7 +170,7 @@ def test_wavy(self):
         # # stator_hub.plot2D()
 
         # # Tip Geometry
-        # stator_tip = airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
+        # stator_tip = Airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
         # stator_tip.le_thickness_add(0.04)
         # ps_height = [0.0500,0.0200,-0.0100]
         # stator_tip.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2)
@@ -183,7 +184,7 @@ def test_wavy(self):
 
         # # Begin 3D design
         # span = 0.05
-        # stator3D = airfoil3D([stator_hub,stator_tip],[0,1],0.05)
+        # stator3D = Airfoil3D([stator_hub,stator_tip],[0,1],0.05)
         # stator3D.stack(stack_type.trailing_edge)
         # stator3D.lean_add([0, 0.05, 0], [0,0.5,1])
         # stator3D.create_blade(100,100,20)
@@ -216,7 +217,7 @@ def test_wavy_whisker(self):
             Wavy blade that maintains cross sectional area
         '''
         # Hub Geometry
-        stator_hub = airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
+        stator_hub = Airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
         stator_hub.le_thickness_add(0.04)
         ps_height = [0.0500,0.0200,-0.0100]
         stator_hub.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2) 
@@ -230,7 +231,7 @@ def test_wavy_whisker(self):
         # stator_hub.plot2D()
 
         # Tip Geometry
-        stator_tip = airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
+        stator_tip = Airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
         stator_tip.le_thickness_add(0.04)
         ps_height = [0.0500,0.0200,-0.0100]
         stator_tip.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2)
@@ -270,12 +271,12 @@ def test_wavy_whisker(self):
         pass
 
     def test_import_geometry(self):
-        # rotor = airfoil3D.import_geometry(folder='import_7%',axial_chord=124) # Set axial chord to 124 mm 
+        # rotor = Airfoil3D.import_geometry(folder='import_7%',axial_chord=124) # Set axial chord to 124 mm 
         # rotor.plot3D_ly()
         pass
 
     def test_imported_blade_shell(self):
-        # rotor = airfoil3D.import_geometry(folder='import_7%',axial_chord=124,span=114,ss_ps_split=105) 
+        # rotor = Airfoil3D.import_geometry(folder='import_7%',axial_chord=124,span=114,ss_ps_split=105) 
         # rotor.rotate(90)
         # # [ss_x_new,ss_y_new,ss_z,ps_x_new,ps_y_new,ps_z] = rotor.get_shell_2D(percent_span=0.5,shell_thickness=-4)
         # rotor.plot_shell_2D(percent_span=0.0,shell_thickness=-3)
@@ -286,7 +287,7 @@ def test_blade_shell(self):
             You can create 2D shell from a 3D Design
         '''
         # # Hub Geometry
-        # stator_hub = airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
+        # stator_hub = Airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58)
         # stator_hub.le_thickness_add(0.04)
         # ps_height = [0.0500,0.0200,-0.0100]
         # stator_hub.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2) 
@@ -300,7 +301,7 @@ def test_blade_shell(self):
         # # stator_hub.plot2D()
 
         # # Tip Geometry
-        # stator_tip = airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
+        # stator_tip = Airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
         # stator_tip.le_thickness_add(0.04)
         # ps_height = [0.0500,0.0200,-0.0100]
         # stator_tip.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2)
@@ -314,7 +315,7 @@ def test_blade_shell(self):
 
         # # Begin 3D design
         # span = 0.05
-        # stator3D = airfoil3D([stator_hub,stator_tip],[0,1],0.05)
+        # stator3D = Airfoil3D([stator_hub,stator_tip],[0,1],0.05)
         # stator3D.stack(stack_type.trailing_edge)
         # stator3D.lean_add([0, 0.05, 0], [0,0.5,1])
         # stator3D.create_blade(100,100,20)
@@ -329,7 +330,7 @@ def test_channel_2D(self):
         '''
         # Stator Hub Geometry
         cax_stator = 0.038
-        stator_hub = airfoil2D(alpha1=0,alpha2=72,axial_chord=cax_stator,stagger=58)
+        stator_hub = Airfoil2D(alpha1=0,alpha2=72,axial_chord=cax_stator,stagger=58)
         stator_hub.le_thickness_add(0.04)
         ps_height = [0.0500,0.0200,-0.0100]
         stator_hub.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2) 
@@ -343,7 +344,7 @@ def test_channel_2D(self):
         # stator_hub.plot2D()
 
         # Stator Tip Geometry
-        stator_tip = airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
+        stator_tip = Airfoil2D(alpha1=5,alpha2=72,axial_chord=0.036,stagger=56)
         stator_tip.le_thickness_add(0.04)
         ps_height = [0.0500,0.0200,-0.0100]
         stator_tip.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2)
@@ -357,15 +358,15 @@ def test_channel_2D(self):
 
         # Begin Stator 3D design
         stator_span = cax_stator
-        stator3D = airfoil3D([stator_hub,stator_tip],[0,1],stator_span)
+        stator3D = Airfoil3D([stator_hub,stator_tip],[0,1],stator_span)
         stator3D.stack(stack_type.trailing_edge)
         stator3D.lean_add([0, 0.05, 0], [0,0.5,1])
         stator3D.create_blade(100,100,20)
         # stator3D.plot3D()
 
         # Rotor Hub Geometry
         cax_rotor_hub = stator_span
-        rotor_hub = airfoil2D(alpha1=30,alpha2=72,axial_chord=cax_rotor_hub,stagger=40)
+        rotor_hub = Airfoil2D(alpha1=30,alpha2=72,axial_chord=cax_rotor_hub,stagger=40)
         rotor_hub.le_thickness_add(0.04)
         ps_height = [0.0500,0.01,0.05]
         rotor_hub.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2) 
@@ -379,7 +380,7 @@ def test_channel_2D(self):
         #rotor_hub.plot2D()
 
         # Rotor Tip Geometry
-        rotor_tip = airfoil2D(alpha1=30,alpha2=72,axial_chord=0.036,stagger=45)
+        rotor_tip = Airfoil2D(alpha1=30,alpha2=72,axial_chord=0.036,stagger=45)
         rotor_tip.le_thickness_add(0.04)
         ps_height = [0.0500,0.01,0.05]
         rotor_tip.ps_thickness_add(thicknessArray=ps_height,expansion_ratio=1.2)

tutorials/stl_tutorial/stl_geometry.py

@@ -5,12 +5,12 @@
 import sys
 sys.path.insert(0,'../../')
 import numpy as np
-from pyturbo.aero import airfoil2D
+from pyturbo.aero import Airfoil2D
 from pyturbo.helper import exp_ratio
 from pyturbo.aero import airfoil3D, stack_type
 import matplotlib.pyplot as plt 
 
-stator2D = airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58) # This creates the camberline
+stator2D = Airfoil2D(alpha1=0,alpha2=72,axial_chord=0.038,stagger=58) # This creates the camberline
 
 # Building Leading Edge
 stator2D.le_thickness_add(0.04)