This is the data so far for publication related to the test of the SMARAGD rocket, designed by Peter Madsen. The double test was done Nov 26, 2011. This idea of creating and launching this rocket, which is a minor Copenhagen Suborbitals rocket compared to size and thrust of earlier engines, is to perform a data and telemetry test at altitudes of 30-60 km .

You might want to read this blog post first for additional information.

SMARAGD stage 1 engine:

Mass oxidizer (LNOX): 28 kg

Mass fuel (Polyurethane): 5.3 kg

O/F: 5.3

Grain ports: 19 @ 25 mm each

Grain length: 300 mm

Injector canals: 32 @ 5 mm each

Total impuls = 70500 Ns

ISP = 216 s (based on Cf = 1.4)

C* = 1512 m/s

Thrust phase: 3.4 s (pressure below 1.5 bar)

Thrust: 30kN

Additional info: No active valves.

SMARAGD stage 1 engine:

Mass oxidizer (LNOX): 9 kg

Mass fuel (Polyurethane): 1.5 kg

O/F: 6

Grain ports: 1 @ 40 mm

Grain length: 500 mm

Injector canals: 1 @ 3.5 mm

Total impuls = N/A

ISP = N/A

Thrust: Maybe just take a look at the graph below

Additional info: No active valves

I also suggest interested readers to check out the following image links for further details during burn phases, operation and inspection. Enjoy!

Official Copenhagen Suborbitals link

Steffen Pedersen private photos link

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Kristian von Bengtson