mass flow rate does not change through the engine thus, it's not changed thrust or create thrust(it is kinda tools for create thrust). if u assigned a new mass flow rate your thrust will be changing but the reason for that is changing the momentum of air.
I don't understand half of what you're saying regarding this but thank you for being part of the evolution of aeronautics. People like you that makes America so great.
Hi Aliya! PLEASEEE keep making Aircraft Propulsion videos, I am struggling with my Propulsion course this semester. It's very motivating to hear from a fellow woman in Aerospace engineering. This pushed me to work harder. I love your explanations, keep it up!!
I have subscribed because 1) You explain everything very well and understandable for people like me who are new to learning aerospace and 2) You have a masters degree in Aerospace Engineering so you know what your talking about! PERFECT
Thank you. It is not easy to understand. I have look at those equations so much and mot been able to understand. Your explanation was very good. I would only ask one thing for the future and that is, that after your expalnation you can use real number coupled with a real jet engine. I think that would increase my understand and help me remember the equation if I see it actually used showing a real real. just an idea, Thank you Master Aliya.
2:24 there's a mistake, in the combustion chamber the pressure DOES NOT rise. Maximum pressure in a turbojet (or turbofan) is reached at the outlet of the compressor just before entering the combustion chamber. You can simply verify this by looking at the Brayton cycle. In reality Into the combustion chamber the pressure actually decreases a little bit because of Rayleigh losses.
Hi, thanks for the video. can you demonstrate how to incorporate the fluid mass in the equation? Will the mass of the fluid be inlet or outlet and which velocity do you use it with to get its momentum?
Wonderful video, certainly helped me to better understand the forces acting within a jet engine. Is there a way to calculate the thrust using the temperature of combustion though? I am building a mini turbojet, and the only variable I know for sure is the combustion temperature. Thank you!
Hi Aliya, you explain very nice. Aerospace always fascinate me. thanks for wonderful video. you wear NASA- tshirts . have you worked in nasa projects ?
i understand the continuity equations regarding the mass flow rate, but how are both values of m-dot the same if the exit velocity is increased and air is compressed increasing the velocity?
so IF i have a 65,000 lb plane ... with 2 engines that generate 22,000 lbs of thrust each ....then my thrust of 44,000= mdot(v2-v1)+p2Ae-p1Ai .if I understood that correctly ... how does one find out how FAST this plane could go ... from here
of all the video's i have watched this is actually the first one that is clear and concise ... yeah I subbed because of it ... now to see if I can find the answer to my question in your video's ... or even even recognise the video that my answer might be covered in lol
Мастер дегри, всё круто, все дела, но почему давление в камере сгорания растёт? Это самая большая ошибка новичков, давление после компрессора всегда падает. Об этом пишут во всех книгах.
@@AliyaBurkit Чем больше хотим выделить энергии с горючего, тем больше его надо сжечь; чтоб больше его жечь надо больше окислителя (воздуха); чтоб больше воздуха поступало надо либо увеличить трубу(двигатель) до гигантских размеров, либо поставить механизм сжатия воздуха, тогда размер двигателя будет приемлемым. Чем лучше компрессор - тем больше топлива можем сжечь и получить больше тяги при малых геометрических размерах двигателя. Камера сгорания или жаровая труба имеют выход в сторону турбины, такого сечения, чтобы при горении давление не превысило значение после диффузора компрессора. Если давление в камере сгорания превысит давление на выходе компрессора произойдёт помпаж (surge) двигателя.
Thrust Is provided By ?
A. Rate of change of momentum of air
B. Change in Mass flow rate
A
@@AliyaBurkit but mam....if we change rate of mass flow ....then also must change in thrust of aircraft
mass flow rate does not change through the engine thus, it's not changed thrust or create thrust(it is kinda tools for create thrust). if u assigned a new mass flow rate your thrust will be changing but the reason for that is changing the momentum of air.
@@batuhan3066 yeh brthr u r right
Thanks for explanation mam....
I don't understand half of what you're saying regarding this but thank you for being part of the evolution of aeronautics. People like you that makes America so great.
Hi Aliya! PLEASEEE keep making Aircraft Propulsion videos, I am struggling with my Propulsion course this semester. It's very motivating to hear from a fellow woman in Aerospace engineering. This pushed me to work harder. I love your explanations, keep it up!!
Simple answer and accessible to the general public. Congratulations!
first comment
your channel is best
love from india!!
Thank you for being a subscriber!
You explain very well.
Love from Bangladesh ❤️
Thank you for watching!
Finally propulsion letsgooo!!! Madam please teach all of it including compressors and turbines Thankyou !🙏🏻
Haha, moving on. Thank you for watching!
I was reluctant in studyng Aerospace engineering b4 watchng ur videos, but now i feel like an aerodynamic guru, thanks to ur videos.
Thank you, but there is still so much more to aerodynamics 😅
This channel is incredible.
The way you explain it is really great.
Love from Brazil ❤️🛫✈
Thank you so much!
I have subscribed because 1) You explain everything very well and understandable for people like me who are new to learning aerospace and 2) You have a masters degree in Aerospace Engineering so you know what your talking about! PERFECT
Thank you so much!
Thanks alot Engineer, I will learn a lot from you. So far so good
This channel is a gift! haha
your videos are amazing, thank you so much!! please keep making more videos relating to aerospace engineering, very interesting content
love from sri lanka teacher
Thanks :)
thanks for u teacher not for us u done a great job
you are awesome please continue making more videos. definitely killing that ATG exam with this
Thank you. It is not easy to understand. I have look at those equations so much and mot been able to understand. Your explanation was very good. I would only ask one thing for the future and that is, that after your expalnation you can use real number coupled with a real jet engine. I think that would increase my understand and help me remember the equation if I see it actually used showing a real real. just an idea, Thank you Master Aliya.
Your hard work is more than the views and subscriber you get 😭😭 sad. keep growing love from india
Thank you so much! Will keep going 💪
Thank you so much this video explains everything in a much more clear way compared to others!!
I'm so glad!
First o will get ur help when i will doing mu aerospace graduation. Love u..as friend😀
Great 👍
Your lectures are very lucid and elaborate. Please explain calculation of required thrust for particular airframe. I am from India
We love u man! Especially ur lectures.
Thanks for watching!
Thank you!
2:24 there's a mistake, in the combustion chamber the pressure DOES NOT rise.
Maximum pressure in a turbojet (or turbofan) is reached at the outlet of the compressor just before entering the combustion chamber. You can simply verify this by looking at the Brayton cycle.
In reality Into the combustion chamber the pressure actually decreases a little bit because of Rayleigh losses.
Here I was just trying to learn how to calculate thrust 😮and I was treated to a roller coaster of emotions too
Hello mam , I am anbu studying ame . Your videos use full me very much. I appreciate you. Keep doing well. I am also from India.
Glad to help!
Hi, your video are very good for understanding.
Nicely Explained !!!
Hi, thanks for the video. can you demonstrate how to incorporate the fluid mass in the equation? Will the mass of the fluid be inlet or outlet and which velocity do you use it with to get its momentum?
Favourite ❤️.....which country u belong?...I want to know.....and a QnA video we want
Thanks shoubhik for recommending this channel....loved it
Thanks shoubhik for recommending this channel....Aliya u are making awesome videos keep going...
Thank u guys.... support her.....she is really awesome ❤️
I'm from Kazakhstan
Thank you for joining!
great tutorial thanks
Glad to help
Wow. So SImple. Hopefully you do become a Good Professor
Haha thanks, that's not my goal 😅
Thank you !! 🙂🙂
Welcome!
hello can u make a video on how to drive general GTE formula
Thank you Mam
Most welcome 😊
Wonderful video, certainly helped me to better understand the forces acting within a jet engine. Is there a way to calculate the thrust using the temperature of combustion though? I am building a mini turbojet, and the only variable I know for sure is the combustion temperature. Thank you!
thanks, but in the combustion chamber the pressure remains constant (in ideal cases), in the reality the pressure drops.
Why is the direction of P2Ae opposite the direction of air flow?
Thanks Alia
Thanks for watching!
Your explanation was so vivid, I just can't wait when next one wil come..Stay safe n sound.
Thanks for watching! Next one is coming
what are the casual parameters for the fuel flow ??
Aliya I'm trying my best to figure out those equations, how does the weight factor which has to with gravity fits into the equations?
Why is the units for thrust pound force lbf?
can u explain about hang glider lift. please. I want to understand it properly. no one can teach me better than u. I wish u could be my teacher.
Sis can you tell..is aviation management subject is good for build up caree?..
Great explanation👍🏻
A question: would be the heating of the gasses after the turbine (not with afterburner) generate more thrust?
Great question. No, thrust only depends on how much air and how fast it's leaving the engine. You can't make more air by heating it up
@@AliyaBurkit thank you so much
This is right😅😂
Thank you😉
Hi Aliya, you explain very nice. Aerospace always fascinate me. thanks for wonderful video. you wear NASA- tshirts . have you worked in nasa projects ?
Thank you for watching! No, it's still my dream))
THANKS A LOT TEACHER YOU TEACH BEAUTIFUL ❤️👍
Thank you!
Hi! Do you maybe have a practice example for this equation?
Yes, I will have videos on solving actual problems
What specialization have you done in aerospace engineering master's? Ma'am
Hi sis
Iam Aishwarya, 4th year Aerospace engineering student , I want to connect with u, how can I connect with u?
help me !!! How to calculate thrust of a jet engine through RPM
Hi aliya ....is possible can u make video about Inertia propulsion and scope as well as limitations...
please send me your WhatsApp number or cell number. i will contact you
please upload newtons third law on lift fast
ruclips.net/video/RwN00nYzzvM/видео.html
Please ma'am... When are you doing your next video.... It been a while
Nice explanation, but it's better to have an example. Thanks
Here also an Indian
i understand the continuity equations regarding the mass flow rate, but how are both values of m-dot the same if the exit velocity is increased and air is compressed increasing the velocity?
*if the engine has a centrifuge
Madoum, is aerospace engineering a good profession
I have 99 % in both physics and mathematics.
Can i become a e
so IF i have a 65,000 lb plane ... with 2 engines that generate 22,000 lbs of thrust each ....then my thrust of 44,000= mdot(v2-v1)+p2Ae-p1Ai .if I understood that correctly ... how does one find out how FAST this plane could go ... from here
of all the video's i have watched this is actually the first one that is clear and concise ... yeah I subbed because of it ... now to see if I can find the answer to my question in your video's ... or even even recognise the video that my answer might be covered in lol
You look pretty as always..
Wow, thank you!
@@AliyaBurkit Welcome..😍😍
Мастер дегри, всё круто, все дела, но почему давление в камере сгорания растёт? Это самая большая ошибка новичков, давление после компрессора всегда падает. Об этом пишут во всех книгах.
Зачем тогда компрессор? Давление падает после сгорания, когда уходит дальше
@@AliyaBurkit Чем больше хотим выделить энергии с горючего, тем больше его надо сжечь; чтоб больше его жечь надо больше окислителя (воздуха); чтоб больше воздуха поступало надо либо увеличить трубу(двигатель) до гигантских размеров, либо поставить механизм сжатия воздуха, тогда размер двигателя будет приемлемым.
Чем лучше компрессор - тем больше топлива можем сжечь и получить больше тяги при малых геометрических размерах двигателя.
Камера сгорания или жаровая труба имеют выход в сторону турбины, такого сечения, чтобы при горении давление не превысило значение после диффузора компрессора.
Если давление в камере сгорания превысит давление на выходе компрессора произойдёт помпаж (surge) двигателя.
Hi! Buddy .I'm a aeronautical engineering student from India. I need your support to learn the things effectively. Shall we discuss?
Mam are you American🇺🇸
Wow what a smart elegant beautiful woman... I wish I could meet a woman as educated and talented she is. I could learn from her.
Ur so beautiful
wrong equation
Wrong
hello can u make a video on how to drive general GTE formula