Can I use the load factor to estimate the lift? The Next CEO of Stack OverflowDo any aircraft...
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Can I use the load factor to estimate the lift?
The Next CEO of Stack OverflowDo any aircraft out there use negative lift?What would be the lift formula for straight wings?How can I estimate Roll from Position?Is there any way to estimate the weight difference between a trimmable horizontal stabilizer and a fixed tailplane?What is the definition of load factor & how do you apply it?When calculating the lift coefficient,should I use only the lift provided by wings, or also the net upward forces of the entire aircraft?How can I calculate the lift force on an aircraft pulling out of a dive?Does Buoyant Lift Force scale with Load Factor?When calculating lift, using the the NASA lift equation, can any value be increased, ie. velocity or surface area, for increased lift?Load factor and how does velocity affect it?
$begingroup$
If I have a fixed aircraft as the baseline, then I am not sure the specific flight condition, can I use the load factor to estimate the lift on the wing?
aircraft-design aerodynamics
asked 5 hours ago
Allen HuangAllen Huang
61
New contributor
Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
$endgroup$
add a comment |
$begingroup$
If I have a fixed aircraft as the baseline, then I am not sure the specific flight condition, can I use the load factor to estimate the lift on the wing?
aircraft-design aerodynamics
asked 5 hours ago
Allen HuangAllen Huang
61
New contributor
Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
$endgroup$
$begingroup$
Besides, I can have access to the mass and the mass distribution of the wing.
$endgroup$
– Allen Huang
5 hours ago
add a comment |
$begingroup$
If I have a fixed aircraft as the baseline, then I am not sure the specific flight condition, can I use the load factor to estimate the lift on the wing?
aircraft-design aerodynamics
asked 5 hours ago
Allen HuangAllen Huang
61
New contributor
Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
$endgroup$
If I have a fixed aircraft as the baseline, then I am not sure the specific flight condition, can I use the load factor to estimate the lift on the wing?
aircraft-design aerodynamics
aircraft-design aerodynamics
asked 5 hours ago
Allen HuangAllen Huang
61
New contributor
Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
asked 5 hours ago
Allen HuangAllen Huang
61
New contributor
Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
asked 5 hours ago
Allen HuangAllen Huang
61
New contributor
Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
asked 5 hours ago
Allen HuangAllen Huang
61
asked 5 hours ago
Allen HuangAllen Huang
61
61
New contributor
Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
New contributor
Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
Check out our Code of Conduct.
$begingroup$
Besides, I can have access to the mass and the mass distribution of the wing.
$endgroup$
– Allen Huang
5 hours ago
add a comment |
$begingroup$
Besides, I can have access to the mass and the mass distribution of the wing.
$endgroup$
– Allen Huang
5 hours ago
$begingroup$
Besides, I can have access to the mass and the mass distribution of the wing.
$endgroup$
– Allen Huang
5 hours ago
$begingroup$
Besides, I can have access to the mass and the mass distribution of the wing.
$endgroup$
– Allen Huang
5 hours ago
add a comment |
2 Answers
2
active
oldest
votes
$begingroup$
If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.
answered 4 hours ago
Carlo FelicioneCarlo Felicione
43k478155
$endgroup$
$begingroup$
The lift you get from that includes the lift from the fuselage and the tailplane. And it is a vector sum so yes the tailplane does matter.
$endgroup$
– Ville Niemi
4 hours ago
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
3 hours ago
$begingroup$
Do you mean the load factor that I get from the handbook is the total load factor not just the load factor for the wing?
$endgroup$
– Allen Huang
3 hours ago
$begingroup$
@CarloFelicione Yes, the reason I commented is because the question spoke about lift of the wing. But you can discuss that with Allen.
$endgroup$
– Ville Niemi
3 hours ago
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
2 hours ago
add a comment |
$begingroup$
If you know where the CG is, and where the aerodynamic centers of the wing and the tail are (I am assuming a traditional configuration) so you know the distance from the aero center of the wing to the CG = d_wing, and similar for the tail, and you know the moment the wing generates (ignore the moment about the tail...it is small), and you know the load factor, then you can figure out the total lift generated by the wing. You have two equations:
Sum of moments about CG = 0 (constant pitch rate)
d_wing x liftWing + d_tail x liftTail + wingMoment = 0
Sum of lifts equals load factor times weight of aircraft
liftWing + liftTail = loadFactor x weight
Now solve for liftWing.
answered 1 hour ago
MikeYMikeY
47616
$endgroup$
add a comment |
Your Answer
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2 Answers
2
active
oldest
votes
2 Answers
2
active
oldest
votes
active
oldest
votes
active
oldest
votes
$begingroup$
If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.
answered 4 hours ago
Carlo FelicioneCarlo Felicione
43k478155
$endgroup$
$begingroup$
The lift you get from that includes the lift from the fuselage and the tailplane. And it is a vector sum so yes the tailplane does matter.
$endgroup$
– Ville Niemi
4 hours ago
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
3 hours ago
$begingroup$
Do you mean the load factor that I get from the handbook is the total load factor not just the load factor for the wing?
$endgroup$
– Allen Huang
3 hours ago
$begingroup$
@CarloFelicione Yes, the reason I commented is because the question spoke about lift of the wing. But you can discuss that with Allen.
$endgroup$
– Ville Niemi
3 hours ago
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
2 hours ago
add a comment |
$begingroup$
If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.
answered 4 hours ago
Carlo FelicioneCarlo Felicione
43k478155
$endgroup$
$begingroup$
The lift you get from that includes the lift from the fuselage and the tailplane. And it is a vector sum so yes the tailplane does matter.
$endgroup$
– Ville Niemi
4 hours ago
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
3 hours ago
$begingroup$
Do you mean the load factor that I get from the handbook is the total load factor not just the load factor for the wing?
$endgroup$
– Allen Huang
3 hours ago
$begingroup$
@CarloFelicione Yes, the reason I commented is because the question spoke about lift of the wing. But you can discuss that with Allen.
$endgroup$
– Ville Niemi
3 hours ago
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
2 hours ago
add a comment |
$begingroup$
If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.
answered 4 hours ago
Carlo FelicioneCarlo Felicione
43k478155
$endgroup$
If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.
answered 4 hours ago
Carlo FelicioneCarlo Felicione
43k478155
answered 4 hours ago
Carlo FelicioneCarlo Felicione
43k478155
answered 4 hours ago
Carlo FelicioneCarlo Felicione
43k478155
answered 4 hours ago
Carlo FelicioneCarlo Felicione
43k478155
43k478155
$begingroup$
The lift you get from that includes the lift from the fuselage and the tailplane. And it is a vector sum so yes the tailplane does matter.
$endgroup$
– Ville Niemi
4 hours ago
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
3 hours ago
$begingroup$
Do you mean the load factor that I get from the handbook is the total load factor not just the load factor for the wing?
$endgroup$
– Allen Huang
3 hours ago
$begingroup$
@CarloFelicione Yes, the reason I commented is because the question spoke about lift of the wing. But you can discuss that with Allen.
$endgroup$
– Ville Niemi
3 hours ago
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
2 hours ago
add a comment |
$begingroup$
The lift you get from that includes the lift from the fuselage and the tailplane. And it is a vector sum so yes the tailplane does matter.
$endgroup$
– Ville Niemi
4 hours ago
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
3 hours ago
$begingroup$
Do you mean the load factor that I get from the handbook is the total load factor not just the load factor for the wing?
$endgroup$
– Allen Huang
3 hours ago
$begingroup$
@CarloFelicione Yes, the reason I commented is because the question spoke about lift of the wing. But you can discuss that with Allen.
$endgroup$
– Ville Niemi
3 hours ago
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
2 hours ago
$begingroup$
The lift you get from that includes the lift from the fuselage and the tailplane. And it is a vector sum so yes the tailplane does matter.
$endgroup$
– Ville Niemi
4 hours ago
$begingroup$
The lift you get from that includes the lift from the fuselage and the tailplane. And it is a vector sum so yes the tailplane does matter.
$endgroup$
– Ville Niemi
4 hours ago
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
3 hours ago
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
3 hours ago
$begingroup$
Do you mean the load factor that I get from the handbook is the total load factor not just the load factor for the wing?
$endgroup$
– Allen Huang
3 hours ago
$begingroup$
Do you mean the load factor that I get from the handbook is the total load factor not just the load factor for the wing?
$endgroup$
– Allen Huang
3 hours ago
$begingroup$
@CarloFelicione Yes, the reason I commented is because the question spoke about lift of the wing. But you can discuss that with Allen.
$endgroup$
– Ville Niemi
3 hours ago
$begingroup$
@CarloFelicione Yes, the reason I commented is because the question spoke about lift of the wing. But you can discuss that with Allen.
$endgroup$
– Ville Niemi
3 hours ago
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
2 hours ago
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
2 hours ago
add a comment |
$begingroup$
If you know where the CG is, and where the aerodynamic centers of the wing and the tail are (I am assuming a traditional configuration) so you know the distance from the aero center of the wing to the CG = d_wing, and similar for the tail, and you know the moment the wing generates (ignore the moment about the tail...it is small), and you know the load factor, then you can figure out the total lift generated by the wing. You have two equations:
Sum of moments about CG = 0 (constant pitch rate)
d_wing x liftWing + d_tail x liftTail + wingMoment = 0
Sum of lifts equals load factor times weight of aircraft
liftWing + liftTail = loadFactor x weight
Now solve for liftWing.
answered 1 hour ago
MikeYMikeY
47616
$endgroup$
add a comment |
$begingroup$
If you know where the CG is, and where the aerodynamic centers of the wing and the tail are (I am assuming a traditional configuration) so you know the distance from the aero center of the wing to the CG = d_wing, and similar for the tail, and you know the moment the wing generates (ignore the moment about the tail...it is small), and you know the load factor, then you can figure out the total lift generated by the wing. You have two equations:
Sum of moments about CG = 0 (constant pitch rate)
d_wing x liftWing + d_tail x liftTail + wingMoment = 0
Sum of lifts equals load factor times weight of aircraft
liftWing + liftTail = loadFactor x weight
Now solve for liftWing.
answered 1 hour ago
MikeYMikeY
47616
$endgroup$
add a comment |
$begingroup$
If you know where the CG is, and where the aerodynamic centers of the wing and the tail are (I am assuming a traditional configuration) so you know the distance from the aero center of the wing to the CG = d_wing, and similar for the tail, and you know the moment the wing generates (ignore the moment about the tail...it is small), and you know the load factor, then you can figure out the total lift generated by the wing. You have two equations:
Sum of moments about CG = 0 (constant pitch rate)
d_wing x liftWing + d_tail x liftTail + wingMoment = 0
Sum of lifts equals load factor times weight of aircraft
liftWing + liftTail = loadFactor x weight
Now solve for liftWing.
answered 1 hour ago
MikeYMikeY
47616
$endgroup$
If you know where the CG is, and where the aerodynamic centers of the wing and the tail are (I am assuming a traditional configuration) so you know the distance from the aero center of the wing to the CG = d_wing, and similar for the tail, and you know the moment the wing generates (ignore the moment about the tail...it is small), and you know the load factor, then you can figure out the total lift generated by the wing. You have two equations:
Sum of moments about CG = 0 (constant pitch rate)
d_wing x liftWing + d_tail x liftTail + wingMoment = 0
Sum of lifts equals load factor times weight of aircraft
liftWing + liftTail = loadFactor x weight
Now solve for liftWing.
answered 1 hour ago
MikeYMikeY
47616
answered 1 hour ago
MikeYMikeY
47616
answered 1 hour ago
MikeYMikeY
47616
answered 1 hour ago
MikeYMikeY
47616
47616
add a comment |
add a comment |
Allen Huang is a new contributor. Be nice, and check out our Code of Conduct.
Allen Huang is a new contributor. Be nice, and check out our Code of Conduct.
Allen Huang is a new contributor. Be nice, and check out our Code of Conduct.
Allen Huang is a new contributor. Be nice, and check out our Code of Conduct.
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$begingroup$
Besides, I can have access to the mass and the mass distribution of the wing.
$endgroup$
– Allen Huang
5 hours ago