Engine Design : Three [3]

[stephanielue8088]

🎏 Objective

[ ] We want to prepare 3 engine designs by using NASA CEA and RPA

🚀 What do the engine design not include?

• Material type
• Ablative
• Do not worry about the diameter of the chamber at the entrance

🚵‍♀️ Process

1. Use NASA CEA to obtain O/F versus Temperature graphs for the chamber. We have done this before. For reference, see [this link] (https://usfedu.sharepoint.com/:w:/t/SocietyofAeronauticsandRocketryGRP/ER_gVfd0j9lJj7vr4aOE_sEBXf1dhCWeJ4l9PvSao0hlrA?e=IP666x). Here, use the Chamber Pressure specified in Table 1.0 Chamber Pressure – Thrust Combinations.
2. Open RPA
3. Open Engine Definition. ➡️ Enter the value for Chamber Pressure ➡️ Enter the value for "nominal thrust" into RPA according to the thrust specified in Table 1.0 Chamber Pressure – Thrust Combinations.
4. Open Propellent Specifications ➡️Add liquid nitrous oxide and liquid 95% ethanol
5. Open Nozzle Flow Model ➡️ For Nozzle Exit Condition, set this to 1.01325 atm
6. Hit Run
7. Open Engine Design >> Chamber Geometry >> Design Parameters* ➡️ Record the Characteristic Length L
8. Engine Design >> Chamber Geometry >> Size and Geometry ➡️Record Dc (chamber diameter)

❓ What Do I do with this information?

Save the file an upload here for analysis later.

❓ How do I know whether or not I should make another simulation

1. In NASA CEA, check if Maximum temperature after O/F Temperature analysis is no greater than 2900K
2. In RPA, check that L* = 66 inches = 1676 mm ~ 1-2 m

[!TIP] See if you can simulate the rocket in [OLD] Base 11 Preliminary Request for Static Test Fire.pdf Video

[stephanielue8088]

@stephanielue8088 Create a template for which to put this information on.

[stephanielue8088]

Please see Engine Designs here