I have a question If an altimeter setting is not available, the pilot can set the altimeter to the airport's field elevation before takeoff. is this true?
Yes, but the setting should be cross checked with an altimeter setting at a nearby field, and adjusted in flight based on ATC report. I have a broken altimeter at home, that I can set to read the accurate elevation of my town, but i wouldn’t want to take off with it!
You sort of got one thing wrong. You said that if lift and weight are equal, the airplane will maintain altitude, and that if the lift is greater than weight it will climb, if less than it will descend. If lift and weight are equal, the plane will maintain its inertial reference frame. If a plane is ascending or descending at a constant speed, lift and weight are equal. So if your plane is ascending at let's say 5 feet per minute, and lift and weight equalize, it will continue ascending at 5 fpm. It won't level off until weight exceeds lift for long enough to change the reference frame and then the two match each other again. An aircraft can ascend or descend while keeping the forces balanced. When the forces are imbalanced acceleration occurs. When they're in balance it doesn't. You got that about the horizontal plane but it's the same for the vertical, even though I realize that's confusing to many.
Yes! Acceleration is key in all four directions. So if lift and weight are equal, the airplane will maintain altitude OR rate of climb/descent. When one is greater than the other the rate of climb/descent reverses. A climb becomes a descent and vice versa. The key for the questions on the test is that the forces are in equilibrium in “unaccelerated” flight. Kinda crude boiling down aerodynamics to a few multiple choice questions huh? Thanks for the comment/correction
FlightInsight right! Putting all those college physics courses to use in the UA-cam comments. And here my dad said we wasted a bunch of money on my tuition! Also it said that if lift exceeds weight it will climb. It may just instead decelerate it’s descent, etc. You understand that and maybe the test makers don’t include that. I guess inertial reference frames are beyond the scope of a pilot’s license :)
Remember, this is what you need to know to pass the test. Thus, the total nonsense explanation of lift 1:10. A real explanation here: ua-cam.com/video/aa2kBZAoXg0/v-deo.html, but that won't help you with an FAA test.
…Lift and weight are not equal in either the steady climb or descent. In the climb you have vector sum of lift and thrust equal and opposite to weight. In the descent you have vector sum of lift and drag equal and opposite to weight. Hence the well known result that excess thrust determines climb angle, γ, and lift/drag ratio determines glide angle (also γ). In both cases, the magnitude of lift is slightly less than weight. The lift vector being defined as perpendicular to the flight path, it can itself only directly oppose weight during level flight.
I have a question, how come some aircraft like the cl13 have a engine that produces 7000 pounds of thrust but the empty weight of the aircraft is around 10,000 and still fly.
Off if anybody is preparing to take the written exam. The first videos in this series are not anywhere or if any relevance whatsoever. If you don't know what produces lyft or understand the basics of flight, you're not ready to take the test.
great explanation and visuals! keep up the good work :D
I have a question
If an altimeter setting is not available, the pilot can set the altimeter to the airport's field elevation before takeoff. is this true?
Yes, but the setting should be cross checked with an altimeter setting at a nearby field, and adjusted in flight based on ATC report. I have a broken altimeter at home, that I can set to read the accurate elevation of my town, but i wouldn’t want to take off with it!
Thank you for the response. Love your channel, by the way.
You sort of got one thing wrong. You said that if lift and weight are equal, the airplane will maintain altitude, and that if the lift is greater than weight it will climb, if less than it will descend.
If lift and weight are equal, the plane will maintain its inertial reference frame. If a plane is ascending or descending at a constant speed, lift and weight are equal. So if your plane is ascending at let's say 5 feet per minute, and lift and weight equalize, it will continue ascending at 5 fpm. It won't level off until weight exceeds lift for long enough to change the reference frame and then the two match each other again. An aircraft can ascend or descend while keeping the forces balanced.
When the forces are imbalanced acceleration occurs. When they're in balance it doesn't. You got that about the horizontal plane but it's the same for the vertical, even though I realize that's confusing to many.
Yes! Acceleration is key in all four directions. So if lift and weight are equal, the airplane will maintain altitude OR rate of climb/descent. When one is greater than the other the rate of climb/descent reverses. A climb becomes a descent and vice versa.
The key for the questions on the test is that the forces are in equilibrium in “unaccelerated” flight. Kinda crude boiling down aerodynamics to a few multiple choice questions huh?
Thanks for the comment/correction
FlightInsight right! Putting all those college physics courses to use in the UA-cam comments. And here my dad said we wasted a bunch of money on my tuition!
Also it said that if lift exceeds weight it will climb. It may just instead decelerate it’s descent, etc. You understand that and maybe the test makers don’t include that. I guess inertial reference frames are beyond the scope of a pilot’s license :)
Remember, this is what you need to know to pass the test. Thus, the total nonsense explanation of lift 1:10. A real explanation here: ua-cam.com/video/aa2kBZAoXg0/v-deo.html, but that won't help you with an FAA test.
U are alive
…Lift and weight are not equal in either the steady climb or descent. In the climb you have vector sum of lift and thrust equal and opposite to weight. In the descent you have vector sum of lift and drag equal and opposite to weight. Hence the well known result that excess thrust determines climb angle, γ, and lift/drag ratio determines glide angle (also γ). In both cases, the magnitude of lift is slightly less than weight. The lift vector being defined as perpendicular to the flight path, it can itself only directly oppose weight during level flight.
I have a question, how come some aircraft like the cl13 have a engine that produces 7000 pounds of thrust but the empty weight of the aircraft is around 10,000 and still fly.
Why do you think that thrust must equal weight for flight? The video certainly doesn't suggest such a thing.
@@neverfox thanks for reminding of comment I made 2 years ago
@@theentirestateofalaska.4983lol
I’m going to say. Lift and Thrust.
Off if anybody is preparing to take the written exam. The first videos in this series are not anywhere or if any relevance whatsoever. If you don't know what produces lyft or understand the basics of flight, you're not ready to take the test.
If you can’t spell or don’t have the respect for developing pilots you probably shouldn’t post your shitty opinions