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- Видео 61
- Просмотров 172 649
Brian Kish
Добавлен 23 сен 2014
Видео
Lateral/Directional Dynamic Stability
Просмотров 2,2 тыс.4 года назад
Lateral/Directional Dynamic Stability
Solving the Aircraft Equations of Motion
Просмотров 7 тыс.4 года назад
Solving the Aircraft Equations of Motion
2 Basic Aerodynamics and Pitot Statics
Просмотров 7765 лет назад
2 Basic Aerodynamics and Pitot Statics
1 Introduction to Aircraft Performance
Просмотров 4,9 тыс.5 лет назад
1 Introduction to Aircraft Performance
Helicopter Lifting Off From FIT Aviation
Просмотров 1485 лет назад
Helicopter Lifting Off From FIT Aviation
Dynamic Lateral Directional Stability and Control
Просмотров 1,2 тыс.6 лет назад
Dynamic Lateral Directional Stability and Control
thanks for the video sir🫡
Just as I predicted. It looks like a Rectangular wing . And stall occurs first at the wing root trailing edge. Therefore the tufts in that location are the first to experience turbulent flow.
This class was really impressive. You gave me an holistic overview of aeronautical engineering. Thank you so much.
Very underrated video. Explains nichols chart excellently. Cheers :)
I just want you to know that your videos are absolutely incredible. I am an Aerospace student and this is helping me so much to understand what is going on in my stab/Con class, thank you so much for making this
I´m currently a LFTE student at EuroFlightTest and I´m happy to prepare myself with your presentations, Brian. Thanks a lot
Brian, I am teaching Aerodynamics this Fall at FIT and was wondering if I can get a copy of your slide deck. Jim
Thanks ❤
Thanks a lot
Nice Please I have an question Consider a jet-engine powered executive aircraft flying at an altitude of 2000ft, speed of 100ms-1 and having the following characteristics: Wingspan - 16.3m Wing area - 29.54m2 Normal gross weight - 88,124N Parasite drag coefficient CD-0 - 0.02 Oswald efficiency factor e - 0.81 Powerplant - 2 turbofan engines of 16,300N of thrust each Fuel capacity - 4236ltrs of kerosene Specific fuel consumption - 0.6lb of fuel/(lb of thrust)(h) Calculate the following at level unaccelerated flight: Aircraft lift coefficient (CL) 0.52 Total drag coefficient 0.032 Thrust required to maintain level unaccelerated flight (TR) 5,423.02N Excess thrust available at level unaccelerated flight 27,176.98N Endurance of aircraft 12.75hrs Range of aircraft
Sir are V(c.g.) and V(true) equal?
👏 Brilliant
Hi, can you help me with some questions, I am struggling on how to calculating cg margins on an aircraft?
Systematic presentation, Thank you
Thank you so much <3
What is the right hand rule the prof. is mentioning ?
The moment causing the aircraft to pitch down has negative sign and vice versa. It is in agreement with general right hand rule for moments f.e. in static analysis of cantilever beam (clockwise rotation has a negative sign...).
And maybe prof. probably recalls the right hand rule of gyroscopic effect for propeller
Thank you teacher you are amazing
Thanks, it was reaally useful
Mr Brian, I am very interesting with this video. I have a question, can i improve phugoid stability and longitudinal static stability with these methods on the mechanical FCS aircraft. Thanks
Thanks!
Thank you for your information
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Thank you for providing all these videos related to Flight Testing! I'm leaving this comment to tell You that at 15:04 there is a typo in the pitching moment differential equation. Thank you again!
Hi Brian! That video is so useful. I Need to know if you can explain the difference to use that method for an airplane with a fixed pitch propeller. Thank you!!
Was this on the characteristics of that particular airplane, which looks like a PIPER PA-28-161 Warrior?
Thank you so much!
Interesting video, wish there were more like this.
Good lecture. You wouldn't believe how much you've helped me!
NOICEEEEEE
When I try to manually calculate the feedback loop, it's always different from matlab, why's that? I'm using the generic formula that would be Gclose(s)=G/1+GH but it's different for some reason
Hi, because it is not the same. Here you can find a direct comparsion between feedback and G=G/(1+GH): de.mathworks.com/help/control/ug/using-feedback-to-close-feedback-loops.html#d122e14003 Iam trying also to figure out, how the feedback loop is mathematically implemented. I think that their is a Pole-Zero-Simplification performed in the feedback function, but Iam not sure...
nice video thank you
Thank you! This was very insightful!
Awesome knowledge provided by you 👍👍 Thanks
i realize it is kinda off topic but does anybody know of a good website to stream new tv shows online?
@Hayes Waylon try FlixZone. You can find it on google =)
how to find the aerodynamic center of the wing experimentally ?
Usually it's a quarter chord length from the leading edge of the airfoil. In addition the aerodynamic center does not change with variation in angle of attack.
Thanks so much! Saved me for my controls final tomorrow.
You shouldn't put your microphone in your washing machine while recording yourself
Thanks a lot!
Hi, Thanks for the video. how can you find bandwidth frequency without matlab? 3:40
bandwidth frequency is frequency w that makes closed-loop gain equal to around 0.707 and solve that w for that closed-loop gain will get the answer.
thank you very much Sir
merci
i got the idea thanks, its help me alot :)
life saver Thank you so much
Thank you Mr.Kish, it is very descriptive.
would it not be less complicated to simply change your den for CLTF to [1 14 95 100 0]? never the less, thanks for the video
thanks alot
thank you! great work!!!
This is really helpful!! Thanks a lot!
Thank You :) great video
Thank you so much! you saved me!