Johan M
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- TL;DR
- My goal is to understand why EDF thrust increases when the outlet area of a thrust tube increases for static thrust. The formula I've seen for static thrust depends on outlet velocity and mass flowrate; mass flowrate is constant, and increased outlet area would decrease velocity wrt bernoulli, so I am uncertain why some RC forums say other wise
Hi everyone. I am tasked with making an EDF rocket for a university project. The end of the rocket has a set of flaps that redirect air to control the rockets trajectory, seen in the image. The 90mm EDF itself is located near region 1.
. I would like to know why, the physics behind it, a smaller outlet area of a thrust tube results in a higher thrust. I have posted this question on a separate RC forum :https://www.rcgroups.com/forums/showthread.php?3931737-EDF-Thrust-tube-theory#post47447981 but I still felt uncertainty. One of the members stated: "Remember an exhaust nozzle increases the back pressure so the fan has to do more work. The energy going into the fan is unchanged so as the pressure rises the mass flow reduces''. I can see why the back pressure would increase through bernoulli, but I don't understand why the mass flow rate reduces; the smaller area and larger velocity work out to the same flowrate, also seen below:
From the same textbook of the above picture, the thrust formula below was found:
It seemed to solely depend on exit velocity (For static thrust I've seen V0 can be taken as zero). I would appreciate any advice in this regard, thanks.
From the same textbook of the above picture, the thrust formula below was found:
It seemed to solely depend on exit velocity (For static thrust I've seen V0 can be taken as zero). I would appreciate any advice in this regard, thanks.