NACA 23015 and NACA 23012 - Fusion360 Script Python (Cessna 310N)

NACA23012.py

import adsk.core, adsk.fusion, adsk.cam, traceback, math

def run(context):
    ui = None
    try:
        app = adsk.core.Application.get()
        ui = app.userInterface
        design = app.activeProduct

        # Get the active sketch
        sketch_airfoil = adsk.fusion.Sketch.cast(app.activeEditObject)
        if not sketch_airfoil:
            ui.messageBox('Please select a sketch first')
            return

        # NACA 23012 airfoil parameters
        max_camber = 0.03  # 3% of chord length
        max_camber_position = 0.3  # 30% of chord length
        max_thickness = 0.12  # 12% of chord length

        # Number of points to generate for the airfoil
        num_points = 100
        chord_length = 119.6  # Set the chord length to 990.6 mm

        # Function to calculate the thickness distribution
        def thickness_distribution(x):
            return (5 * max_thickness) * (
                0.2969 * math.sqrt(x) -
                0.1260 * x -
                0.3516 * x**2 +
                0.2843 * x**3 -
                0.1015 * x**4
            )

        # Function to calculate camber line
        def camber_line(x):
            if x < max_camber_position:
                return (max_camber / (max_camber_position**2)) * (2 * max_camber_position * x - x**2)
            else:
                return (max_camber / ((1 - max_camber_position)**2)) * ((1 - 2 * max_camber_position) + 2 * max_camber_position * x - x**2)

        # Function to calculate the slope of the camber line
        def camber_line_slope(x):
            if x < max_camber_position:
                return (2 * max_camber / (max_camber_position**2)) * (max_camber_position - x)
            else:
                return (2 * max_camber / ((1 - max_camber_position)**2)) * (max_camber_position - x)

        # Generate upper and lower surface points
        upper_surface_coords = []
        lower_surface_coords = []
        for i in range(num_points + 1):
            x = (i / num_points) * chord_length  # Scale x-coordinate to match chord length in mm
            y_camber = camber_line(x / chord_length) * chord_length  # Scale camber line to mm
            dyc_dx = camber_line_slope(x / chord_length)
            theta = math.atan(dyc_dx)
            y_thickness = thickness_distribution(x / chord_length) * chord_length

            # Upper surface points
            x_upper = x - y_thickness * math.sin(theta)
            y_upper = y_camber + y_thickness * math.cos(theta)
            upper_surface_coords.append((x_upper, y_upper))

        for i in range(num_points, -1, -1):
            x = (i / num_points) * chord_length  # Scale x-coordinate to match chord length in mm
            y_camber = camber_line(x / chord_length) * chord_length  # Scale camber line to mm
            dyc_dx = camber_line_slope(x / chord_length)
            theta = math.atan(dyc_dx)
            y_thickness = thickness_distribution(x / chord_length) * chord_length

            # Lower surface points
            x_lower = x + y_thickness * math.sin(theta)
            y_lower = y_camber - y_thickness * math.cos(theta)
            lower_surface_coords.append((x_lower, y_lower))

        # Convert coordinates to Point3D objects and adjust for sketch
        upper_points = []
        for coord in upper_surface_coords:
            point = adsk.core.Point3D.create(coord[0] - chord_length / 2, -coord[1], 0)
            upper_points.append(point)

        lower_points = []
        for coord in lower_surface_coords:
            point = adsk.core.Point3D.create(coord[0] - chord_length / 2, -coord[1], 0)
            lower_points.append(point)

        # Create ObjectCollections for the points
        upper_point_collection = adsk.core.ObjectCollection.create()
        for point in upper_points:
            upper_point_collection.add(point)

        lower_point_collection = adsk.core.ObjectCollection.create()
        for point in lower_points:
            lower_point_collection.add(point)

        # Create splines for upper and lower surfaces
        upper_spline = sketch_airfoil.sketchCurves.sketchFittedSplines.add(upper_point_collection)
        lower_spline = sketch_airfoil.sketchCurves.sketchFittedSplines.add(lower_point_collection)

        # Connect the endpoints to close the airfoil profile
        sketch_airfoil.sketchCurves.sketchLines.addByTwoPoints(upper_points[0], lower_points[-1])
        sketch_airfoil.sketchCurves.sketchLines.addByTwoPoints(upper_points[-1], lower_points[0])

        ui.messageBox('NACA 23012 airfoil created successfully with smooth splines!')

    except:
        if ui:
            ui.messageBox('Failed:\n{}'.format(traceback.format_exc()))

NACA23015.py

import adsk.core, adsk.fusion, adsk.cam, traceback, math

def run(context):
    ui = None
    try:
        app = adsk.core.Application.get()
        ui = app.userInterface
        design = app.activeProduct

        # Get the active sketch
        sketch_airfoil = adsk.fusion.Sketch.cast(app.activeEditObject)
        if not sketch_airfoil:
            ui.messageBox('Please select a sketch first')
            return

        # NACA 23015 airfoil parameters
        max_camber = 0.03  # 3% of chord length
        max_camber_position = 0.3  # 30% of chord length
        max_thickness = 0.15  # 15% of chord length

        # Number of points to generate for the airfoil
        num_points = 100
        chord_length = 171  # Set the chord length to 2082.8 mm

        # Function to calculate the thickness distribution
        def thickness_distribution(x):
            return (5 * max_thickness) * (
                0.2969 * math.sqrt(x) -
                0.1260 * x -
                0.3516 * x**2 +
                0.2843 * x**3 -
                0.1015 * x**4
            )

        # Function to calculate camber line
        def camber_line(x):
            if x < max_camber_position:
                return (max_camber / (max_camber_position**2)) * (2 * max_camber_position * x - x**2)
            else:
                return (max_camber / ((1 - max_camber_position)**2)) * ((1 - 2 * max_camber_position) + 2 * max_camber_position * x - x**2)

        # Function to calculate the slope of the camber line
        def camber_line_slope(x):
            if x < max_camber_position:
                return (2 * max_camber / (max_camber_position**2)) * (max_camber_position - x)
            else:
                return (2 * max_camber / ((1 - max_camber_position)**2)) * (max_camber_position - x)

        # Generate upper and lower surface points
        upper_surface_coords = []
        lower_surface_coords = []
        for i in range(num_points + 1):
            x = (i / num_points) * chord_length  # Scale x-coordinate to match chord length in mm
            y_camber = camber_line(x / chord_length) * chord_length  # Scale camber line to mm
            dyc_dx = camber_line_slope(x / chord_length)
            theta = math.atan(dyc_dx)
            y_thickness = thickness_distribution(x / chord_length) * chord_length

            # Upper surface points
            x_upper = x - y_thickness * math.sin(theta)
            y_upper = y_camber + y_thickness * math.cos(theta)
            upper_surface_coords.append((x_upper, y_upper))

        for i in range(num_points, -1, -1):
            x = (i / num_points) * chord_length  # Scale x-coordinate to match chord length in mm
            y_camber = camber_line(x / chord_length) * chord_length  # Scale camber line to mm
            dyc_dx = camber_line_slope(x / chord_length)
            theta = math.atan(dyc_dx)
            y_thickness = thickness_distribution(x / chord_length) * chord_length

            # Lower surface points
            x_lower = x + y_thickness * math.sin(theta)
            y_lower = y_camber - y_thickness * math.cos(theta)
            lower_surface_coords.append((x_lower, y_lower))

        # Convert coordinates to Point3D objects and adjust for sketch
        upper_points = []
        for coord in upper_surface_coords:
            point = adsk.core.Point3D.create(coord[0] - chord_length / 2, -coord[1], 0)
            upper_points.append(point)

        lower_points = []
        for coord in lower_surface_coords:
            point = adsk.core.Point3D.create(coord[0] - chord_length / 2, -coord[1], 0)
            lower_points.append(point)

        # Create ObjectCollections for the points
        upper_point_collection = adsk.core.ObjectCollection.create()
        for point in upper_points:
            upper_point_collection.add(point)

        lower_point_collection = adsk.core.ObjectCollection.create()
        for point in lower_points:
            lower_point_collection.add(point)

        # Create splines for upper and lower surfaces
        upper_spline = sketch_airfoil.sketchCurves.sketchFittedSplines.add(upper_point_collection)
        lower_spline = sketch_airfoil.sketchCurves.sketchFittedSplines.add(lower_point_collection)

        # Connect the endpoints to close the airfoil profile
        sketch_airfoil.sketchCurves.sketchLines.addByTwoPoints(upper_points[0], lower_points[-1])
        sketch_airfoil.sketchCurves.sketchLines.addByTwoPoints(upper_points[-1], lower_points[0])

        ui.messageBox('NACA 23015 airfoil created successfully with smooth splines!')

    except:
        if ui:
            ui.messageBox('Failed:\n{}'.format(traceback.format_exc()))