O/F = w_{o}/w_{f}  (1)
I_{sp} = thust/total propellant flow rate  (2)
w_{t} = F/I_{sp} = 100/244 = 0.41lb/sec  (3)
w_{o} = w_{t}r/(r + 1) = 0.293lb/sec  (4)
w_{f} = w_{t}/(r + 1) = 0.117lb/sec  (5)
w_{t} = w_{o} + w_{f}  (6)
A_{t} = w_{t}/P_{t}\sqrt{RT_{t}/γg_{c}}  (7)
T_{t} = T_{c} [\frac{1}{1 + \frac{γ−1}{2}} ]  (8)
T_{t} = (.909)(T_{c})  (9)
T (^{o}R) = T (^{o}F) + 460  (10)
P_{t} = P_{c} [1 + \frac{γ − 1}{2}]^{− \frac{γ}{γ−1}}  (11)
P_{t} = (.564)(P_{c})  (12)
M_{e}^{2} = \frac{2}{γ − 1} [(\frac{P_{c}}{P_{atm}} )^{\frac{γ−1}{γ}} − 1]  (13)

A_{e} = \frac{A_{t}}{M_{e}} [\frac{1 + \frac{γ−1}{2} M_{e}^{2}}{(γ + 1)/2} ]^{\frac{γ+1}{2(γ−1)}}  (14)
A_{c} = A_{t}(A_{e}/A_{t})  (15)
T_{e} = T_{c}(T_{e}/T_{c})  (16)
D_{t} = \sqrt{4A_{t}/π}  (17)
D_{e} = \sqrt{4A_{e}/π}  (18)
L∗ = V_{c}/A_{t}  (19)
A_{c} = D_{c}^{2}/4  (20)
V_{c} = 1.1(A_{c}L_{c})  (21)
S = P D/2t_{w}  (22)
t_{w} = P D/16000  (23)
Q = qA = w_{w}c_{p}(T − T_{i})  (24)
w = C_{d}A\sqrt{2gρΔP}  (25)
v = C_{d}\sqrt{2g(ΔP/ρ)}  (26)