Cl max is just the maximum coefficient of lift a wing can make for it's given shape and size. I don't know how it is calculated as it is some very clever aerodynamics that go into it. Maybe this video will help, if you can get over the robotic sounding voice! ruclips.net/video/qftxYth-DxQ/видео.html
Never. CofP for lift and drag. CofG for weight. Through the engines for thrust. If the CofP and CofG were located in the same position then all of the forces except thrust would act through the same point...
The best ATPL classes ever. I'm so greatful for these videos.
Your lections are better than our ground school keep it up you are really helping ppl out.
This is great! Thanks for sharing :)
Man you're phenomenal in your intro's hahahhah
I love this intros
@atplclass, can you make one more video that explains the CL, CLmax etc.
Cl max is just the maximum coefficient of lift a wing can make for it's given shape and size. I don't know how it is calculated as it is some very clever aerodynamics that go into it. Maybe this video will help, if you can get over the robotic sounding voice! ruclips.net/video/qftxYth-DxQ/видео.html
@@atplclass Thanks 😊
in what case all forces act through CG?
Never. CofP for lift and drag. CofG for weight. Through the engines for thrust.
If the CofP and CofG were located in the same position then all of the forces except thrust would act through the same point...
In the summary part you made a mistake. The lift has to be greater than the weight in a climb. L>W
Other than that thanks for your work, keep it up!
no it doesn't, because some of the engine thrust points upwards counteracting the weight of the aircraft that acts straight down