Air Standard Flow

AIM= TO draw the air standard flow diagram

Main code

import math
import matplotlib.pyplot as plt

def Engine_kinematics(bore,stroke,con_rod,cr,start_crank,end_crank):

	a=stroke/2
	R=con_rod/a

	V_s=math.pi*(1/4)*pow(bore,2)*stroke
	V_c=V_s/(cr-1)

	sc=math.radians(start_crank)
	ec=math.radians(end_crank)

	num_values=50
	dtheat=(ec-sc)/(num_values-1)
	V=[]
#Creating the loop for the formula
	for i in range(0,num_values):
		theta=sc+i*dtheat
		term1=0.5*(cr-1)
		term2=R+1-math.cos(theta)
		term3=pow(R,2)-pow(math.sin(theta),2)
		term3=pow(term3,0.5)

		V.append((1+term1*(term2-term3))*V_c)
	return V	

#inputs
p1=101325
t1=500
t3=2300
gamma=1.4
bore=0.1
stroke=0.1
con_rod=0.15
cr=8

v_s=(math.pi/4)*pow(bore,2)*stroke
v_c=v_s/(cr-1)
v1=v_c+v_s
v2=v_c

#all 4 stages
p2=p1*pow(v1,gamma)/pow(v2,gamma)
rhs=p1*v1/t1
t2=p2*v2/rhs
V_compression=Engine_kinematics(bore,stroke,con_rod,cr,180,0)
constant=p1*pow(v1,gamma)
print(constant)

P_compression=[]

for v in V_compression:
	P_compression.append(constant/pow(v,gamma))

v3=v2
rhs=p2*v2/t2
p3=rhs*t3/v3
V_expansion=Engine_kinematics(bore,stroke,con_rod,cr,0,180)
constant=p3*pow(v3,gamma)
print(constant)

P_expansion=[]

for v in V_expansion:
	P_expansion.append(constant/pow(v,gamma))

v4=v1
p4=p3*pow(v3,gamma)/pow(v4,gamma)
t4=p4*v4/rhs

#ploting the figure
plt.plot([v2,v3],[p2,p3])
plt.plot(V_compression,P_compression)
plt.plot(V_expansion,P_expansion)
plt.plot([v4,v1],[p4,p1])
plt.xlabel('volume')
plt.ylabel('pressure')
plt.show()

OUTPUT

Programe for the thermal efficiency

import numpy as np 
from scipy.integrate import odeint
import matplotlib.pyplot as plt
import math

cr=np.linspace(0,10,100)
gamma=1.5

etta=1-1/pow(cr,(gamma-1))

plt.plot(cr,etta,linewidth=3)
plt.xlabel('compression ratio')
plt.ylabel('theramal efficiency')
plt.show()

Output