MiG-29
Banned Idiot
hahaha minute 17:00 is nozzle hahaha is not an intake, where is the free stream flow? hahahaha
Free stream is free not in a tube, in fact spilled air never enters the intake
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SDF Aerospace and Aerodynamics Corner
- Thread starter paintgun
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Free stream is free not in a tube, in fact spilled air never enters the intake
Engineer
Major
Nope. Pressure recovery ratio of DSI is not only better than that of F-104, but is also better than 2D variable-geometry inlet with three shock waves. F-4D and many aircraft in that era employs that same type of variable-geometry inlet.
Engineer
Major
Nope. Whether the intake is fixed or has variable-geometry does not make the throat acts as a regulator to flow rate. This is due to the compressibility of air itself and the Bernoulli's effect.
Engineer
Major
LOL! I love seeing you get all desperate when your bullshit breaks down in the presence of facts.
A nozzle that is reversed is an intake, and vice-versa. The direction in which air travels does not alter how compressible fluid behaves in a throat. In fact, starting at the video explains how supersonic inlet works based on the same principle as a nozzle.
You clearly do not know what you are talking about if you don't even know about this fact. Oh, that's right, you don't know about Benoulli's principle and the fact that air is compressible either. Here is a suggestion for you: stop inventing pseudo-aerodynamic theories.
The inside of an inlet is not free stream. And whether it is a free stream has no relevance on how compressible fluid behaves in throat area. As air passes through the narrower space of the throat, it is compressed due to the compressibility property of air. The presence of shock waves is an evidence of that compressibility property. The air also speeds up, due to Bernoulli's principle, and this is seen in the pressure distribution also shown by the video.
The throat does not act as a regulator of air flow, contrary to what you said.
A nozzle that is reversed is an intake, and vice-versa. The direction in which air travels does not alter how compressible fluid behaves in a throat. In fact, starting at the video explains how supersonic inlet works based on the same principle as a nozzle.
You clearly do not know what you are talking about if you don't even know about this fact. Oh, that's right, you don't know about Benoulli's principle and the fact that air is compressible either. Here is a suggestion for you: stop inventing pseudo-aerodynamic theories.
The inside of an inlet is not free stream. And whether it is a free stream has no relevance on how compressible fluid behaves in throat area. As air passes through the narrower space of the throat, it is compressed due to the compressibility property of air. The presence of shock waves is an evidence of that compressibility property. The air also speeds up, due to Bernoulli's principle, and this is seen in the pressure distribution also shown by the video.
The throat does not act as a regulator of air flow, contrary to what you said.
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MiG-29
Banned Idiot
nope because the spilled air never enters the intake duct, what the video shows is a duct where the first throat is fixed thus the mass entering the first fixed throat has to remain fixed at the exit of the second variable throat and by the way that is a nozzle.
On a intake as F-14 or Sr-71 you have free stream air and a throat opening or closing, the fact air is spilling shows the Ao/A1 can change. this mass free stream has different spill rates.
MiG-29
Banned Idiot
LOL! I love seeing you get all desperate when your bullshit breaks down in the presence of facts.
A nozzle that is reversed is an intake, and vice-versa. The direction in which air travels does not alter how compressible fluid behaves in a throat. In fact, starting at the video explains how supersonic inlet works based on the same principle as a nozzle.
You clearly do not know what you are talking about if you don't even know about this fact. Oh, that's right, you don't know about Benoulli's principle and the fact that air is compressible either. Here is a suggestion for you: stop inventing pseudo-aerodynamic theories.
The inside of an inlet is not free stream. And whether it is a free stream has no relevance on how compressible fluid behaves in throat area. As air passes through the narrower space of the throat, it is compressed due to the compressibility property of air. The presence of shock waves is an evidence of that compressibility property. The air also speeds up, due to Bernoulli's principle, and this is seen in the pressure distribution also shown by the video.
The throat does not act as a regulator of air flow, contrary to what you said.
The nozzle is not a intake, and that is your fallacy, the nozzle has an entrance fixed mass area that mass remain fixed because it is a closed circuit, from entrance throat to exit throat air is fixed; an intake is different because of the free stream the intake can take different amounts of air depending on throat area and it can spill air, the nozzle can not spill air it is a closed circuit
in fact it only will spill air hahaha if you open a bypass door hahaha
Engineer
Major
Spill air doesn't enter the inlet, but the amount of air flowing through the mouth is still the same as the amount of air flowing through the throat. Mass flow rate of mi is equal to ms, as shown here:
The video shows that, essentially showing what is occurring inside the duct. The video even says mass flow rate is fixed numerous times.
The inside of an inlet is not free stream air. Variation in throat size has no influence on the flow rate whatsoever.
Engineer
Major
Nope. There is no fallacy in my statement. A nozzle which is reversed is an inlet, and vice-versa, because compressible fluids such as air do not behave differently when the direction of flow is changed. The only difference is that in the inlet case supersonic flow is upstream, while in the nozzle case supersonic flow is downstream. The video explained that the same principle used in a nozzle is applied for inlet.
The only fallacy is your assumption of variation in throat size changes the amount of flow to argue that variation in throat size changes the amount of flow. This is called .
Bypass door is what regulates flow. On the F-22, we see the inlets have bypass doors but no variable-geometry throat. A variable-geometry inlet on the other hand, must have bypass doors. Hence, variable-geometry does not regulate flow.
MiG-29
Banned Idiot
you argument is a total fallacy because at different speeds you get different mass flow rates on an intake, if you would get always a rate of one or Ao/A1=1 means the mass is fixed.
while on the video you have a fixed throat delivering the same mass of flow to a variable throat, and in fact in order to change the mass flow you will need bypass doors hahahaha
MiG-29
Banned Idiot
Spill air doesn't enter the inlet, but the amount of air flowing through the mouth is still the same as the amount of air flowing through the throat. Mass flow rate of mi is equal to ms, as shown here:
The video shows that, essentially showing what is occurring inside the duct. The video even says mass flow rate is fixed numerous times.
The inside of an inlet is not free stream air. Variation in throat size has no influence on the flow rate whatsoever.
spill air never enters the throat and it varies according to the speed, spill air is like a sink overflowing, you like it or not hahaha