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







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Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
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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
















1












$begingroup$


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







share|improve this question







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














1












1








1


1



$begingroup$


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







share|improve this question







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






share|improve this question







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.











share|improve this question







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.









share|improve this question




share|improve this question






New contributor




Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
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asked 5 hours ago









Allen HuangAllen Huang

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Allen Huang is a new contributor to this site. Take care in asking for clarification, commenting, and answering.
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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


















  • $begingroup$
    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










2 Answers
2






active

oldest

votes


















1












$begingroup$

If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.






share|improve this answer









$endgroup$













  • $begingroup$
    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
    2 hours ago










  • $begingroup$
    @CarloFelicione Could you tell me how to get the load factor for the wing?
    $endgroup$
    – Allen Huang
    2 hours ago



















1












$begingroup$

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.






share|improve this answer









$endgroup$














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    2 Answers
    2






    active

    oldest

    votes








    2 Answers
    2






    active

    oldest

    votes









    active

    oldest

    votes






    active

    oldest

    votes









    1












    $begingroup$

    If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.






    share|improve this answer









    $endgroup$













    • $begingroup$
      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
      2 hours ago










    • $begingroup$
      @CarloFelicione Could you tell me how to get the load factor for the wing?
      $endgroup$
      – Allen Huang
      2 hours ago
















    1












    $begingroup$

    If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.






    share|improve this answer









    $endgroup$













    • $begingroup$
      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
      2 hours ago










    • $begingroup$
      @CarloFelicione Could you tell me how to get the load factor for the wing?
      $endgroup$
      – Allen Huang
      2 hours ago














    1












    1








    1





    $begingroup$

    If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.






    share|improve this answer









    $endgroup$



    If you mean total lift force, then yes you can as Lift = Load Factor * Aircraft Weight.







    share|improve this answer












    share|improve this answer



    share|improve this answer










    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
      2 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










    • $begingroup$
      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
      2 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
    2 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
    2 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











    1












    $begingroup$

    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.






    share|improve this answer









    $endgroup$


















      1












      $begingroup$

      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.






      share|improve this answer









      $endgroup$
















        1












        1








        1





        $begingroup$

        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.






        share|improve this answer









        $endgroup$



        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.







        share|improve this answer












        share|improve this answer



        share|improve this answer










        answered 1 hour ago









        MikeYMikeY

        47616




        47616






















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