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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 ?

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

Jevol provides the complete solution for vehicle inspection center, workshop.

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

nice video thank you

Thank you! This was very insightful!

Awesome knowledge provided by you 👍👍 Thanks

how to find the aerodynamic center of the wing experimentally ?

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

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!