![Some thoughts on aero choking in a pipe. [2128x1117 - 341KB]](https://pic8.co/sh/l83YQ9.jpg){kind=link}
Derrrr, numbers are pretty.
Derrrr, numbers are pretty.
In this image we see a normal shockwave in a pipe, the pressure builds at the inlet, and chokes at the throat as the fluid reaches mach 1. We call it choked because the pressure builds up and the pressure terminates in a shockwave, downstream the pressure drops. Along the wall we see as the pipe widens, the pressure drops at the wall, but raises at the center. The pressure at the center is caused by secondary shockwaves by the supersonic flow along the wall reflecting and adding to the drag caused by the primary shockwave. You can see in the first image the expansion fan is weaker and the reflecting compression waves are also weaker leading to a more uniform flow downstream.
The bottom image where the normal shock is strongest has the strongest compression waves from the expansion fans, creating in effect a constriction in a supersonic flow. In compressible/trans/super sonic flows constrictions raise pressure and slow down airflow. It is only after the bulk airflow passes this constriction that the overall pipe pressure decreases. Had the wall been constructed more carefully, one could largely avoid the compression waves while maintaining the expansion fans that further accelerate a choked flow. This would reduce losses substantially.
In the bottom image if you look closely you can see the recirculation bubble.
In this image we see a normal shockwave in a pipe, the pressure builds at the inlet, and chokes at the throat as the fluid reaches mach 1. We call it choked because the pressure builds up and the pressure terminates in a shockwave, downstream the pressure drops. Along the wall we see as the pipe widens, the pressure drops at the wall, but raises at the center. The pressure at the center is caused by secondary shockwaves by the supersonic flow along the wall reflecting and adding to the drag caused by the primary shockwave. You can see in the first image the expansion fan is weaker and the reflecting compression waves are also weaker leading to a more uniform flow downstream.
The bottom image where the normal shock is strongest has the strongest compression waves from the expansion fans, creating in effect a constriction in a supersonic flow. In compressible/trans/super sonic flows constrictions raise pressure and slow down airflow. It is only after the bulk airflow passes this constriction that the overall pipe pressure decreases. Had the wall been constructed more carefully, one could largely avoid the compression waves while maintaining the expansion fans that further accelerate a choked flow. This would reduce losses substantially.
In the bottom image if you look closely you can see the recirculation bubble.
Sure, but what’s the application? Exhaust?
Sure, but what’s the application? Exhaust?
Aerodynamics, underbody aero. You'd be surprised how easy it is to get aero choking in small passages, especially when aided by ground effect. Just the physical act of driving over a mass of air compresses it to an extent, that compression creates a venturi effect where the air tries to escape and return to its original state as quickly as possible.
I learned this when using pitot tubes to validate HVAC systems, we were wondering why the readings and predicted airflow weren't matching up, turns out the shape of the ducting was accelerating air enough to choke the pitot tubes giving us faulty readings. Our own stupidity opened up greater understanding.
Aerodynamics, underbody aero. You'd be surprised how easy it is to get aero choking in small passages, especially when aided by ground effect. Just the physical act of driving over a mass of air compresses it to an extent, that compression creates a venturi effect where the air tries to escape and return to its original state as quickly as possible.
I learned this when using pitot tubes to validate HVAC systems, we were wondering why the readings and predicted airflow weren't matching up, turns out the shape of the ducting was accelerating air enough to choke the pitot tubes giving us faulty readings. Our own stupidity opened up greater understanding.
Ah. Yes, Ive had that as well. Airflow must be measured in a non transition zone. Exhausts approaching supersonic speed behave a bit differently, and the loss of temperature and volume is offsettable with tapered pipe and insulation. The boundary layers are fun to play with, I came up with a neat way of dealing with them that worked both low and high rpm with gains on both. The prototypes broke all the normal rules, at some point I may build a few more and patent them.
Ah. Yes, Ive had that as well. Airflow must be measured in a non transition zone. Exhausts approaching supersonic speed behave a bit differently, and the loss of temperature and volume is offsettable with tapered pipe and insulation. The boundary layers are fun to play with, I came up with a neat way of dealing with them that worked both low and high rpm with gains on both. The prototypes broke all the normal rules, at some point I may build a few more and patent them.
Yep if the temps go down it's easier to get sonic choking, hot air is less dense which is the equivalent of increasing cross sectional area. Hotter temps means it takes more to reach mach 1, so keeping the exhaust nice and hot buys you some wiggle room. Once you get sonic choking, the boundary layer shows you the shape you need to make the wall in order to get max efficiency. You just have to run the thing at the flow rate you want, then capture the boundary layer (PID/Schlerien/CFD), then design the walls to mimic the shape of the BL, then you cut losses dramatically. The flow can just follow the wall curvature instead of creating losses to define its own path of least resistance. You basically make it easy for the flow, and it keeps accelerating.
https://share.southbox.de/f.php?h=1RMD9k4o&p=1
You'd think that it's only a coincidence that this cross sectional schematic looks like the plan form of a bird?
Yep if the temps go down it's easier to get sonic choking, hot air is less dense which is the equivalent of increasing cross sectional area. Hotter temps means it takes more to reach mach 1, so keeping the exhaust nice and hot buys you some wiggle room. Once you get sonic choking, the boundary layer shows you the shape you need to make the wall in order to get max efficiency. You just have to run the thing at the flow rate you want, then capture the boundary layer (PID/Schlerien/CFD), then design the walls to mimic the shape of the BL, then you cut losses dramatically. The flow can just follow the wall curvature instead of creating losses to define its own path of least resistance. You basically make it easy for the flow, and it keeps accelerating.
https://share.southbox.de/f.php?h=1RMD9k4o&p=1
You'd think that it's only a coincidence that this cross sectional schematic looks like the plan form of a bird?
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