![UQx Hypers301x Hypersonics](/img/default-banner.jpg)
- 78
- 594 780
UQx Hypers301x Hypersonics
Registrace 19. 01. 2014
Understand flight at speeds greater than Mach 5 and discover how to analyse the performance of a scramjet.
This is a past/archived course. At this time, you can only explore this course in a self-paced fashion. Certain features of this course may not be active, but many people enjoy watching the videos and working with the materials. Make sure to check for reruns of this course.
A flow is called hypersonic if the Mach number is greater than 5. This means that the flow speed is more than five times the speed of sound. In air at room temperature, the speed of sound is around 340 m/s, so a Mach 5 flow would have a flow speed of 1.7 km/s or just over 6,000 km/h. When a rocket launches a satellite into earth orbit, when a probe enters the atmosphere of another planet or when an aircraft is propelled by a supersonic combustion ramjet engine (a scramjet), hypersonic flows are encountered. Hypersonics - from Shock Waves to Scramjets intr
This is a past/archived course. At this time, you can only explore this course in a self-paced fashion. Certain features of this course may not be active, but many people enjoy watching the videos and working with the materials. Make sure to check for reruns of this course.
A flow is called hypersonic if the Mach number is greater than 5. This means that the flow speed is more than five times the speed of sound. In air at room temperature, the speed of sound is around 340 m/s, so a Mach 5 flow would have a flow speed of 1.7 km/s or just over 6,000 km/h. When a rocket launches a satellite into earth orbit, when a probe enters the atmosphere of another planet or when an aircraft is propelled by a supersonic combustion ramjet engine (a scramjet), hypersonic flows are encountered. Hypersonics - from Shock Waves to Scramjets intr
Video
UQxHYPERS301x 5.4.1 Hypersonic Flight Configurations-
zhlédnutí 2,3KPřed 9 lety
UQxHYPERS301x 5.4.1 Hypersonic Flight Configurations-
UQx HYPERS301X 5.2.4 High Temperature Effects - Density and Kinetics-
zhlédnutí 2,1KPřed 9 lety
UQx HYPERS301X 5.2.4 High Temperature Effects - Density and Kinetics-
UQx HYPERS301x 5.3.2 Mach Number Independence-
zhlédnutí 1,2KPřed 9 lety
UQx HYPERS301x 5.3.2 Mach Number Independence-
UQx HYPERS301x 7.1.1 Project Specification
zhlédnutí 2,2KPřed 10 lety
UQx HYPERS301x 7.1.1 Project Specification
UQxHYPERS301x 7.1.3 Analysis - Step by Step
zhlédnutí 1,6KPřed 10 lety
UQxHYPERS301x 7.1.3 Analysis - Step by Step
UQx HYPERS301x 6.2.1 History of Scramjets
zhlédnutí 3,6KPřed 10 lety
UQx HYPERS301x 6.2.1 History of Scramjets
UQx Hypers301x 6.6.1 Future Challenges for Scramjets
zhlédnutí 2KPřed 10 lety
UQx Hypers301x 6.6.1 Future Challenges for Scramjets
UQx Hypers301x 6.3.1 Scramjet Performance Analysis
zhlédnutí 4,3KPřed 10 lety
UQx Hypers301x 6.3.1 Scramjet Performance Analysis
HYPERS301x 6 6 2 Scramjet Launch animation
zhlédnutí 3,1KPřed 10 lety
HYPERS301x 6 6 2 Scramjet Launch animation
UQX HYPERS301X 6.1.1 Beginners Guide to Scramjets
zhlédnutí 3,1KPřed 10 lety
UQX HYPERS301X 6.1.1 Beginners Guide to Scramjets
UQxHYPERS301x 5.7.1 Impulse Facilities
zhlédnutí 1,6KPřed 10 lety
UQxHYPERS301x 5.7.1 Impulse Facilities
UQx Hypers301x 5.1.1v Beginners Guide to Hypersonic Flow
zhlédnutí 3,6KPřed 10 lety
UQx Hypers301x 5.1.1v Beginners Guide to Hypersonic Flow
UQx Hypers301x 5.2.1v Advanced Guide to Hypersonic Flow
zhlédnutí 4,3KPřed 10 lety
UQx Hypers301x 5.2.1v Advanced Guide to Hypersonic Flow
UQx HYPERS301x 5.4.1 Hypersonic Equivalence Principle
zhlédnutí 2KPřed 10 lety
UQx HYPERS301x 5.4.1 Hypersonic Equivalence Principle
UQx HYPERS301x 4.1.1 Beginners Guide to Friction Flow
zhlédnutí 6KPřed 10 lety
UQx HYPERS301x 4.1.1 Beginners Guide to Friction Flow
UQx Hypers301x 4.2.3.1 Flow Friction Example Problem
zhlédnutí 7KPřed 10 lety
UQx Hypers301x 4.2.3.1 Flow Friction Example Problem
UQx Hypers301x 4.3.3.1 Heat Flow Addition Example Problem
zhlédnutí 4,2KPřed 10 lety
UQx Hypers301x 4.3.3.1 Heat Flow Addition Example Problem
UQx HYPERS301x 4.2.3 Interpretation of Results of Friction Model
zhlédnutí 3,4KPřed 10 lety
UQx HYPERS301x 4.2.3 Interpretation of Results of Friction Model
UQx Hypers301x 4.3.4.1 Stoichiometry Worked Example
zhlédnutí 2,1KPřed 10 lety
UQx Hypers301x 4.3.4.1 Stoichiometry Worked Example
UQx HYPERS301x 4.2.2 Mathematical Model of Flow with Friction
zhlédnutí 4,8KPřed 10 lety
UQx HYPERS301x 4.2.2 Mathematical Model of Flow with Friction
UQx HYPERS301x 4.3.3 Interpretation of Results Heat Addition
zhlédnutí 2,5KPřed 10 lety
UQx HYPERS301x 4.3.3 Interpretation of Results Heat Addition
UQx Hypers301x 4.3.2v Mathmatical Model and Solution
zhlédnutí 3KPřed 10 lety
UQx Hypers301x 4.3.2v Mathmatical Model and Solution
3:35 The 'c_p' value is given for air, not fuel. We therefore need to find 'c_p' of fuel (butane) separately and then, add the fuel and air contributions together; as the heat released will increase the temperature of both air and fuel (butane). What you did here is assume that c_p of air is the same as that of butane, which is clearly wrong... Am I right?
As we saw in the graph, there are two theoretical Shock Wave Angles possible for one Flow Deflection Angle, then why is the higher shock wave angle not visible in the Schileren images? Can someone please explain this?
4:00 Shuttle was a fake rocket 🚀
Yes thank you.
Need to add in mg and drag to model a rocket launch
at 7:36 the temperature ratio is incorrect. It should be 2/(y+1)
Your great video helped me a lot. Thank you so much
Excellent 👍
Could you elaborate more on heat transfer when it comes to re-entry? -Nice table at the end.
I believe you kind of answered it, yet my question is regarding pressure increase?
Say I have an engine with 60 seconds of specific impulse, does that basically mean the same as "If I expend all of the energy that this rocket has, I will get 60 seconds of positive boost in a given direction?"
Literally answered my question thank you!!
Amazingly intuituve video! Deepest gratitude 🙏🙏
Well the guy running might be an idiot but he's capable of running 5 km/s.. that's pretty impressive
Wonderful explanation Sir. I want to join in your group Sir. Could you please suggest me?
5:45
This is sooooo cool!
I couldn't understand well, why is he using Helium... It's not clear from the recording.
Amazing explanation and the Aussie accents makes it even better
A little hilarious to see your calm and gentle look after the last section ^^
0:45 Burrrrrn
How your operating at different mach numbers
for what does the "d" in "pmp" stand for?
Prof needs to drink more water
Hypersonic🚀
Please link the previous video youre talking about jet engines.
La claridad del curso es fantastica, muchas gracias por compartirlo
Choked flow always talks about reducing the back pressure won’t increase m dot once you get sonic flow in the throat. What about increasing the inlet pressure? Surely that will, if you are ramming more in.
Navy
This is actually fun.
need to do it again as iam back of vital information needed to solve here
Does the Shockwave reduce the airflow friction on the surface? (and so less heat is generated?)
Which shape is the ramjet? There's upper lower and ?
But in a pipe (as one example) velocity flow eventually should go into a parabola shape.
Why does the oldest video start with, "Let's continue ..." Where is the starting video?
Thank you so much for this well put together video!
Is there any weird heat conductance at hypersonic speeds? Since it seems like the craft is performing an exothermic reaction (splitting air molecules) which is then heating up the aircraft, is there much loss of heat or is the craft moving so fast that there is little chance for the expulsion of excess heat into the atmosphere?
I see your comment is a year old but I feel compelled to answer because it’s really simple actually. Heat is thermal energy caused by your molecules jumping around. To transfer thermal energy, your molecules must run into something else’s molecules. So if no air is interacting with the craft, all heat gained will stay in the craft.
@@breadwatcher3908 I appreciate your response. My comment may not have been worded the best. One of the major issues with hypersonic flight is heat generated from air resistance. The thing I’ve always found interesting about that is that typically at altitudes where this is possible, the ambient temperature is extremely low. That would make you think there is significant heat loss to the environment. But I guess, in the past year I’ve learned more about sound barriers and whatnot, and based off your comment it seems like in reality the vehicle is not coming into contact with the atmospheric air, but instead the shockwaves are making contact, thereby decreasing the actual ability of the vehicle to offput heat into the environment. This actually might explain a lot. Please correct me if I’m wrong.
@@breadwatcher3908 Just to let you know, I’m also considering atmospheric reentry by spacecraft in this because that is also technically hypersonic flight.
@@breadwatcher3908 there’s a lot of interesting research that could have potential applications to hypersonic flight provided you can develop a solid method for heat transfer. I also wonder about the maneuverability capabilities of these vehicles because you would think that any object operating at those internal temperatures undergoing stress from any deviations in course would structurally compromise the entire air vehicle.
@@casey6104 Ah I understand your question a little better and I believe you’re 99% correct. I’m not an expert on this topic but I don’t think atmospheric reentry is always at supersonic speeds. Even though the atmosphere has a low ambient temp, aircraft heat up during atmospheric reentry(and often times become a big ball of fire) due to drag caused by skin friction. Air molecules can’t move out the way fast enough and just combust. But in supersonic flight, we do not see these crafts engulfed in a big fireball. So I assume there’s a range of speed where you’ll get hotter and hotter because air is having to slide past you, and then a range of speeds where air just doesn’t even touch you due to the higher speed. I think that higher speed makes a shockwave that acts like a barrier pushing the air entirely around you instead of the air sliding past you.
Amazing video, i Have a questione. If I want to reach mach 12 on an experimental plane I have to start with normal jet engines, then switch to ram jets and then finally turn on the scramjets?
The 40 degree wedge example with the curved shock due to expansion fan interaction is wonderful. It finally helped me understand how a strong oblique shock can transition back to the Mach angle in the far field away from the body.
very nice i like thank you everyone. hellovryone
are u indian ? xx
Well explained. Thank you.
I don't agree with your assessment that the space shuttle's solid rocket boosters were reliable. Was this filmed before Jan. 1986?
But how do we know the max. exhaust velocity and max specific impulse?
Why do you plug in the value for L2* in the calculator? If we know that L2* is the point at which the flow becomes choked, why isn't M=1 when you plug in that value?
Av
Claim insurance.
Simple explain of deep concept fabulous
I can't make the algebra work for the equation you have for m-dot, and I can't reproduce the plot for m-dot with either your equation or the one I derived. I get m-dot/p_0 a_0 A_e = P_rat^[g+1/2g] * {2/(g-1) * [P_rat^(1-g/g) - 1]}^1/2 where gamma = g, P_rat is the pressure ratio. Plotting in Desmos, this is only defined for [-1,1] with what I derived. Plotting your equation, it never reaches a maximum. I'm typing up my notes and wanted to include the plots; that's the only reason I noticed.
😷