Air standard Cycle USING PYTHON

import math
import matplotlib.pyplot as plt


def engine_kinematics(bore,stroke,con_rod,cr,start_crank,end_crank):
	\"\"\"
	Engine Kinematics
	\"\"\"

	#Geometric parameters

	a=stroke/2
	R=con_rod/a

	#Volume Parameters
	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

	dtheta=(ec-sc)/(num_values-1)

	V=[]

	for i in range(0,num_values):
		theta=sc+i*dtheta

		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

p1=400
t1=300
t3=1200
gamma=1.4


#Engine parameters 
bore=0.1;
stroke=0.1;
cr=1.7;
con_rod=0.15;

#Swept volume and clearence volume
v_swept=(math.pi/4)*pow(bore,2)*stroke
v_clearence=v_swept/(cr-1)

v1=v_swept+v_clearence
v2=v_clearence

# At state 2
p2=p1*pow(v1,gamma)/pow(v2,gamma)
t2=(p2*v2*t1)/(p1*v1)
kc=p1*pow(v1,gamma)
V_compression=engine_kinematics(bore,stroke,con_rod,cr,180,0)

constant=p1*pow(v1,gamma)

P_compression=[]

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



# At state 3
v3=v2
p3=p2*t3/t2
ke=p3*pow(v3,gamma)
V_expansion=engine_kinematics(bore,stroke,con_rod,cr,0,180)

constant=p3*pow(v3,gamma)

P_expansion=[]

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

# At state 4
v4=v1
p4=p3*pow(v3,gamma)/pow(v4,gamma)
t4=(p4*v2*t1)/(p1*v1)



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.show()

V=engine_kinematics(bore,stroke,con_rod,cr,180,0)

#thermal efficiency

n=1-pow(cr,(1-gamma))
print(n)