# variables
Tw = 32.; # degreeF
d1 = 3.; # in
v = 10.; #fps
delp = 2.; #psi
h1 = 30.; # ft
Tb = 68.; #degreeF
d2 = 1.; #in
h2 = 10.; #ft
# calculations
V = v*(d1/12)*0.0000137/((d2/12)*0.88*0.0000375);
del_p = delp/h2**2 *0.88*V**2;
# results
print 'V = %.2f fps del_p = %.2f psi'%(V,del_p);
import math
# variables
l = 400.; # ft
h = 10.; #ft
v = 30.; # fps
D = 2.; #lb
# calculations
V = math.sqrt((v**2 /l)*h);
D_p = (D/V**2) *(v**2)*(l**2)/h**2;
# results
print 'V = %.2f fps Prototype drag = %d lb'%(V,D_p);
# variables
G = 20000.; #cfs
k = 1./15;
# calculations
Q_m = G*(k)**(2+ 1./2);
# results
print 'Qm = %.f cfs'%(Q_m);
import math
# variables
k = 1./10;
v = 3000.; #fps
h = 15000.; #altitude
T = 68.; # degreeF
am = 870.; #fps
ap = 1057.; #fps
# calculations
Vm = v*(am/ap);
rho_m = v*(1/k)*0.001495*0.031/(0.033*Vm);
p_m = 32.2*rho_m*34.9*(T+460)/(144);
# results
print 'Vm = %d fps p_m = %d psia'%(Vm,p_m);
#rounding-off errors