Python 绘制NACA 4系列翼型

我正试图根据上面描述的公式绘制一个机翼

可以查看此Jupyter笔记本

%matplotlib内联
输入数学
将matplotlib.pyplot导入为pyplot
def法兰（启动、停止、步骤）：
产量起点
首先启动时，
t
应为
0.12
而不是
12
。其次，要使绘图更平滑，请增加采样点

在
numpy
中使用矢量化方法也是一个好主意：

%matplotlib inline
import math
import matplotlib.pyplot as plt
import numpy as np

#https://en.wikipedia.org/wiki/NACA_airfoil#Equation_for_a_cambered_4-digit_NACA_airfoil
def camber_line( x, m, p, c ):
    return np.where((x>=0)&(x<=(c*p)),
                    m * (x / np.power(p,2)) * (2.0 * p - (x / c)),
                    m * ((c - x) / np.power(1-p,2)) * (1.0 + (x / c) - 2.0 * p ))

def dyc_over_dx( x, m, p, c ):
    return np.where((x>=0)&(x<=(c*p)),
                    ((2.0 * m) / np.power(p,2)) * (p - x / c),
                    ((2.0 * m ) / np.power(1-p,2)) * (p - x / c ))

def thickness( x, t, c ):
    term1 =  0.2969 * (np.sqrt(x/c))
    term2 = -0.1260 * (x/c)
    term3 = -0.3516 * np.power(x/c,2)
    term4 =  0.2843 * np.power(x/c,3)
    term5 = -0.1015 * np.power(x/c,4)
    return 5 * t * c * (term1 + term2 + term3 + term4 + term5)

def naca4(x, m, p, t, c=1):
    dyc_dx = dyc_over_dx(x, m, p, c)
    th = np.arctan(dyc_dx)
    yt = thickness(x, t, c)
    yc = camber_line(x, m, p, c)  
    return ((x - yt*np.sin(th), yc + yt*np.cos(th)), 
            (x + yt*np.sin(th), yc - yt*np.cos(th)))


#naca2412 
m = 0.02
p = 0.4
t = 0.12
c = 1.0

x = np.linspace(0,1,200)
for item in naca4(x, m, p, t, c):
    plt.plot(item[0], item[1], 'b')

plt.plot(x, camber_line(x, m, p, c), 'r')
plt.axis('equal')
plt.xlim((-0.05, 1.05))
# figure.set_size_inches(16,16,forward=True)

%matplotlib内联
输入数学
将matplotlib.pyplot作为plt导入
将numpy作为np导入
#https://en.wikipedia.org/wiki/NACA_airfoil#Equation_for_a_cambered_4-digit_NACA_翼型
def外倾角管路（x、m、p、c）：
返回np.where（（x>=0）和（x=0）和（x
%matplotlib inline
import math
import matplotlib.pyplot as plt
import numpy as np

#https://en.wikipedia.org/wiki/NACA_airfoil#Equation_for_a_cambered_4-digit_NACA_airfoil
def camber_line( x, m, p, c ):
    return np.where((x>=0)&(x<=(c*p)),
                    m * (x / np.power(p,2)) * (2.0 * p - (x / c)),
                    m * ((c - x) / np.power(1-p,2)) * (1.0 + (x / c) - 2.0 * p ))

def dyc_over_dx( x, m, p, c ):
    return np.where((x>=0)&(x<=(c*p)),
                    ((2.0 * m) / np.power(p,2)) * (p - x / c),
                    ((2.0 * m ) / np.power(1-p,2)) * (p - x / c ))

def thickness( x, t, c ):
    term1 =  0.2969 * (np.sqrt(x/c))
    term2 = -0.1260 * (x/c)
    term3 = -0.3516 * np.power(x/c,2)
    term4 =  0.2843 * np.power(x/c,3)
    term5 = -0.1015 * np.power(x/c,4)
    return 5 * t * c * (term1 + term2 + term3 + term4 + term5)

def naca4(x, m, p, t, c=1):
    dyc_dx = dyc_over_dx(x, m, p, c)
    th = np.arctan(dyc_dx)
    yt = thickness(x, t, c)
    yc = camber_line(x, m, p, c)  
    return ((x - yt*np.sin(th), yc + yt*np.cos(th)), 
            (x + yt*np.sin(th), yc - yt*np.cos(th)))


#naca2412 
m = 0.02
p = 0.4
t = 0.12
c = 1.0

x = np.linspace(0,1,200)
for item in naca4(x, m, p, t, c):
    plt.plot(item[0], item[1], 'b')

plt.plot(x, camber_line(x, m, p, c), 'r')
plt.axis('equal')
plt.xlim((-0.05, 1.05))
# figure.set_size_inches(16,16,forward=True)