Can I use the load factor to estimate the lift?
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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 Mar 30 at 22:31
Allen HuangAllen Huang
111
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.
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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 Mar 30 at 22:31
Allen HuangAllen Huang
111
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
Mar 30 at 22:32
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 Mar 30 at 22:31
Allen HuangAllen Huang
111
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 Mar 30 at 22:31
Allen HuangAllen Huang
111
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 Mar 30 at 22:31
Allen HuangAllen Huang
111
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 Mar 30 at 22:31
Allen HuangAllen Huang
111
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 Mar 30 at 22:31
Allen HuangAllen Huang
111
asked Mar 30 at 22:31
Allen HuangAllen Huang
111
111
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
Mar 30 at 22:32
add a comment |
$begingroup$
Besides, I can have access to the mass and the mass distribution of the wing.
$endgroup$
– Allen Huang
Mar 30 at 22:32
$begingroup$
Besides, I can have access to the mass and the mass distribution of the wing.
$endgroup$
– Allen Huang
Mar 30 at 22:32
$begingroup$
Besides, I can have access to the mass and the mass distribution of the wing.
$endgroup$
– Allen Huang
Mar 30 at 22:32
add a comment |
2 Answers
2
active
oldest
votes
$begingroup$
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 Mar 31 at 1:57
MikeYMikeY
51616
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add a comment |
$begingroup$
If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.
answered Mar 30 at 23:21
Carlo FelicioneCarlo Felicione
43.2k478155
$endgroup$
$begingroup$
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
Mar 30 at 23:34
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
Mar 31 at 0:11
$begingroup$
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
Mar 31 at 0:35
$begingroup$
@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
Mar 31 at 0:53
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
Mar 31 at 1:30
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 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 Mar 31 at 1:57
MikeYMikeY
51616
$endgroup$
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 Mar 31 at 1:57
MikeYMikeY
51616
$endgroup$
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 Mar 31 at 1:57
MikeYMikeY
51616
$endgroup$
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 Mar 31 at 1:57
MikeYMikeY
51616
answered Mar 31 at 1:57
MikeYMikeY
51616
answered Mar 31 at 1:57
MikeYMikeY
51616
answered Mar 31 at 1:57
MikeYMikeY
51616
51616
add a comment |
add a comment |
$begingroup$
If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.
answered Mar 30 at 23:21
Carlo FelicioneCarlo Felicione
43.2k478155
$endgroup$
$begingroup$
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
Mar 30 at 23:34
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
Mar 31 at 0:11
$begingroup$
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
Mar 31 at 0:35
$begingroup$
@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
Mar 31 at 0:53
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
Mar 31 at 1:30
add a comment |
$begingroup$
If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.
answered Mar 30 at 23:21
Carlo FelicioneCarlo Felicione
43.2k478155
$endgroup$
$begingroup$
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
Mar 30 at 23:34
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
Mar 31 at 0:11
$begingroup$
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
Mar 31 at 0:35
$begingroup$
@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
Mar 31 at 0:53
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
Mar 31 at 1:30
add a comment |
$begingroup$
If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.
answered Mar 30 at 23:21
Carlo FelicioneCarlo Felicione
43.2k478155
$endgroup$
If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.
answered Mar 30 at 23:21
Carlo FelicioneCarlo Felicione
43.2k478155
answered Mar 30 at 23:21
Carlo FelicioneCarlo Felicione
43.2k478155
answered Mar 30 at 23:21
Carlo FelicioneCarlo Felicione
43.2k478155
answered Mar 30 at 23:21
Carlo FelicioneCarlo Felicione
43.2k478155
43.2k478155
$begingroup$
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
Mar 30 at 23:34
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
Mar 31 at 0:11
$begingroup$
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
Mar 31 at 0:35
$begingroup$
@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
Mar 31 at 0:53
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
Mar 31 at 1:30
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
Mar 30 at 23:34
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
Mar 31 at 0:11
$begingroup$
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
Mar 31 at 0:35
$begingroup$
@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
Mar 31 at 0:53
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
Mar 31 at 1:30
$begingroup$
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
Mar 30 at 23:34
$begingroup$
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
Mar 30 at 23:34
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
Mar 31 at 0:11
$begingroup$
That’s what I meant by total lifting force.
$endgroup$
– Carlo Felicione
Mar 31 at 0:11
$begingroup$
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
Mar 31 at 0:35
$begingroup$
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
Mar 31 at 0:35
$begingroup$
@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
Mar 31 at 0:53
$begingroup$
@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
Mar 31 at 0:53
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
Mar 31 at 1:30
$begingroup$
@CarloFelicione Could you tell me how to get the load factor for the wing?
$endgroup$
– Allen Huang
Mar 31 at 1:30
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
Mar 30 at 22:32