# Help needed to design a pulse jet engine.

Does anyone know any Forumulas or how to calculate the dimensions of a pulse jet engine?

I have already built several PULSE JET engines that run by scaling up an existing hobby engine to a larger size. Problem is the scaled up models run but maybe they could run better. I can not find any formulas to design and build a PULSE JET ENGINE. Another problem is pulse jet engines run on air as the oxizider not oxygen like most liquid fuel rocket engines. I can not find any information for using AIR as the oxidizer in a rocket engine. My plan here was to use the formulas to design a liquid fuel rocket engine and use that information to build a Pulse Jet Engine but the physical size of the 100 lb thrust liquid fuel engine is many times smaller than a pulse jet engine so this will not work. I am using Gasoline as the fuel only because it is cheap and easy to get, Alcohol works much better. I am using gaseous oxygen as the oxidizer.

Calculations for a 100 lb thrust liquid fuel rocket engine, gasoline + oxygen.

Isp = Specific Impulse

Wo = lb of oxygen / sec

Wf = Lb of fuel / sec

Wt = wo + wf

Wo = .293 lb / sec

Wf = .117 lb / sec

Wt = .41 lb / sec

Gamma = 1.2

Dc = combustion chamber diameter = .4555"

Lc = combustion chamber length = 2.15"

Dt = nozzle diameter = .238"

Dc = nozzle exit = 1.2"

nozzle angle 15 degrees.

Trial and Error from scaling up a hobby engine to 100 lb Thrust. This works but I think it could work better. I have no idea how efficient my engine is. I have no information on AIR as an oxidizer to determine if my air intake is correct and the combustion chamber is the correct size. Gasoline + Air

Cr = Combustion chamber compression ratio = 2 to 1

Dc = combustion chamber diameter = 5.000""

Lc = combustion chamber length = 6.000"

Ai = Air intake = Dt x .8 = 2.000"

Dt = nozzle diameter = 2.5"

Tl = Tail Pipe length = 27"

Dc = nozzle exit = 3.5"

nozzle angle 15 degrees.

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I have one of about that size. The pipe is missing, so it's difficult to tell. Which means, I have a hunk of aluminum casting, the combustion chamber shell and some reeds.

I have it all figured out. Math is simple and it applies to all size engines. Here are videos. I have run them all for about 2 hours each static thrust no problems reed valves hold up fine. I made some new discoveries how to protect the reed valves from combustion chamber heat. Engines start at 20% thrust and throttle up to 100% static thrust but this is not maximum thrust forward speed produces ram air so the engine can be throttled up to 140% to 150% thrust depending on the speed of the engine and the design of the air intake.

5 lbs thrust. SR-71