The lift formula explained

Airbus 380 or Cessna 172, big or small, they all adhere to the same physical laws. This video shows how the formula for lift can be used to demonstrate the relationship between aircraft weight, airspeed, and angle of attack.
Weight is commonly, but not 100 % correctly, used to describe mass in kilograms (kg). “If my mass is 60 kg, my weight is 60 kg on planet Earth, but only 10 kg on the Moon.” But to be 100 % scientific, we have to use newton to measure weight, because weight is the gravitational force acting on a mass. On planet Earth, 1 kg mass equals 9.8 newtons. Enough said. After this video, I will, like everybody else, refer to weight as kg.
This video is a remake of a video I made some months ago. I have simplified the calculations and corrected some errors. When making the first video, I stumbled into a problem: How could I find the density of the atmosphere when the air is dry? There are dozens of different density calculators online, some are plain wrong, and others cannot calculate the density in kg per cubic meters when the altitude is given in feet. For this video, I selected to use the Atmospheric properties calculator (see the link below).
Attributions:
Airbus S.A.S: Airbus 380 departure.
Gevers Aircraft: Genesis aircraft with telescopic wings.
Jeffrey A. Scott: Drag Coefficient & Lifting Line Theory www.aerospaceweb.org/question/...
John McIver: Cessna Skyhawk performance assessment www.temporal.com.au/c172.pdf
Recommended links:
“Bernoulli or Newton?” • Video
Atmospheric properties calculator: www.aerospaceweb.org/design/sc...
Recommended reading:
John T. Lowry: Performance of light aircraft. ISBN 1563473305, 9781563473302.
Follow Fly with Magnar: / 1140864699685560

[@cruxader27]

The most common question asked in about every pilot job interview. This video is very helpful to those applying for the job. Thank you!

[@gaven6531]

How is it that I only find the most useful and concise videos after I have completed a course, and only when I am not directly searching for it?

[@stvrstc]

Thanks a lot for doing this, this is an unimaginable help for us students. I am currently on my CPL/IR/ATPL theory distance learning course and these videos help realy a great deal, sometimes it is just one small detail that makes a click in my head and i got it, like with this video here. Thank you again and my deepest respect.

[@thomasl7932]

Thanks for the great video, this is very useful for my learning for my ppl exams

[@veloyozh]

Thanks a lot! I tried to find lift formula but everywere I saw it it was without phisical units. Your video greatly helped!

[@loayoraby674]

i had fun watching this video and i learn new things that wasn't clear to me,thanks.

[@autorotate1803]

Best explanation on the internet, thank you!

[@smwagh123]

very good explanation

[@josephcameron530]

Great video!

[@dawninarizonanow9252]

This was helpful and I really didn’t understand lift coefficient.

[@chrissteevens442]

Thanks good explanation.....

[@phyarth8082]

Video try to explain lift just by a drag force, but CL or CD coefficient must be vectorial angle attack must be sine and cosine function accordingly, and must be between 1 and 0, they use velocity v to define that CL coefficient. We can not be defined by velocity angle of attack can be changed relative to x-axis direction, that is a big misconception because is the very optimal angle of attack depending on engine of plane and area. Or more philosophical question do wings need at all? and when wings become drags force to move freely force with higher velocity forward (x-axis) that is a very nice feedback loop math calculation. Drag coefficient CL - is independent of plane velocity or wind in the case of windmills.

[@flywithjericho1902]

thank you sir

[@Barabyk]

Brilliant!

[@modelcraft299]

Very good 😊

[@alsasalsabila5781]

How to calculate the engine power after solving that equation?

[@Peace4life-4everyone]

Clear teaching

[@andrewhale12345]

Thanks for the great video! I have a question regarding lift. If I am climbing in an aircraft and I am able to maintain the same indicated airspeed shouldn't my rate of climb remain constant since my increased velocity (TAS) is compensating for the fall in density? From practice and the POH I know it is not the case but trying to get my head around the theory because in my mind one would assume the same pressure is hitting the pitot tube.

[@halfameerkat1296]

how do you calculate the lift coefficient from the geometry of the wing

[@tzachus]

wow wow wow ....you are stunning