SPECIFICATIONS
For this engine we want to use gaseous oxygen and methanol to produce a thrust of 2224.11 N, using a chamber pressure of 3.45 MPa (500 psi). The initial values are listed on the table below.
F
| 2224.11 |
N
|
Pc
|
3.45
|
MPa
|
Pe
|
101325
|
Pa
|
Tc
|
3643.88
|
K
|
Mixture ratio
|
1.25
| |
Isp
|
248
| s |
R'
|
8314.3
|
J/(kg*kmol*K)
|
𝕸
|
20.744
|
(l/n)
|
Dc/Dt
|
4.75
| |
L*
|
1
|
m
|
γ
|
1.13
| |
gc
|
9.81
|
m/s^2
|
The thrust chamber will be casted in a copper alloy using a technique similar to lost wax, this will reasonably reduce the engine's production cost.
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