www.pulse-jets.com

Is it possible to use the formula for lift: L=q*S*cl? I know all the data for the free turbine blades exept cl. For example: the flow velocity from the guide vanes through the turbine is 200 m/s, the density of air is 2 kg/m3 and the surface area of each turbine blade is 0,0004m2. And we approximate...

Im thinking of building a turboshaft engine with a free power turbine from an old turbocharger. The gas generator core will be build on a centrifugal flow compressor and a radial turbine. Axial guide vanes and one axial turbine will be used as a free turbine stage. I wonder if you guys can help me w...

mach diamonds in the exhaust are COOL, but speak to improper nozzle design... This is interesting! Yes, it seems that the rocket engine have a exit pressure higher than the surrounding atmosperic pressure. But even if the Pe = Pa, shouldnt there be any diamonds in the exaust plume then? Or would th...

Hi :-) I dont have the formulas to calculate how much energi that is needed in order to spin compressors from turbocharges. Hi Hondaen I do not have a complete useful formula for that calculation but I have ideas of how you can approach this problem. If you know the pressure before and the pressure...

Here is a good example of what I mean:

http://www.pulse-jets.com/phpbb2/viewtopic.php?t=3180

Probably the best approch is to apply to some kind of education program, preferably a university. If money is a problem, a scholarship would not be that hard to get.

mk wrote:
However, wouldn't the 2k/(k+1) expression -- wherever it came from -- yield for values γ>k?

No, it wouldn't. It would yield γ<k
This expression can be found in Sutton 7Ed on page 57 and also in most literature dealing with thermodynamics and fluid mechanics. Nothing unique for Sutton.

Thanks for reply.

a=acoustic velocity
vt=throat velocity

I have not found a explanation of the difference yet. But I got a clue using the speed of sound:D If we start with the expression of speed of sound: a = (γ*R*T)^1/2 and continue with the expression of throat velocity in a convergent section, because the nozzle is choked M=1 is the maximum velocity. ...

Thank you for the pics. It must have been a real pleasure to see the monster flying :o

I'd rather have that rejection letter than never to have even tried ;-) Second that! Such a process can be engaged AFTER you get your basic idea protected, if you can. Before you can protect your ideas you have to prove that your idea work by the laws of nature. And again we need some kind of objec...

superhornet59, You dont know what kind of discussion I have had with this guy. Can this guy can be a new genius in the field of propulsion? Of course he can! The problem with this hobby is that people often claims that they are more talented than everybody else. They said they have design something ...

A couple of times every year I notice people that claims they have designed a "ground-breaking" engine. All of them have something in common - all their work is based on highly subjective judgements. When I have mailed and asked for objective qualitative and quantitative facts about projects they an...

That is one hell of a rocket engine :o Do you know what kind of fuel grain configuration and O/F ratio they are using. Seems to be a highly regressive burn in the movie. If I have to guess whats happened to the rocket, I would guess that the explosion was supersonic due to the small fragments of the...

I was watching the live video over the net of Discovery launch 4 july. I noticed the unsmooth burn of the booster rockets compared to the smoother burning liquid fuel SSMEs. The camera picture is somewhat blured by the resonance from the solid fuel motors but instantly when the boosters are released...

I have ordered the book Thermodynamics and mechanics of propulsio from my local library. Maybe I found answers in this book.