What is wing loading?
- Thread starter FlyboyZR1
- Start date
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I've heard/read over and over that wing loading is directly affected with changes in CG ... a forward CG increases wing loading and therefore stalling speed, while an aft CG decreases wing loading/stalling speed ... but what's the definition of "wing loading?"
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It's the amount of lift a wing is generating as related to weight; ie- amount needed to lift the aircraft. It's expressed in pounds per square foot. Take weight of the aircraft divided by wing area. Direct relation is typically lower wing loading = lower AOA needed to generate particular lift coefficient.
I've heard/read over and over that wing loading is directly affected with changes in CG ... a forward CG increases wing loading and therefore stalling speed, while an aft CG decreases wing loading/stalling speed ... but what's the definition of "wing loading?"
[/ QUOTE ]
It's the amount of lift a wing is generating as related to weight; ie- amount needed to lift the aircraft. It's expressed in pounds per square foot. Take weight of the aircraft divided by wing area. Direct relation is typically lower wing loading = lower AOA needed to generate particular lift coefficient.
FlyboyZR1
New Member
[ QUOTE ]
It's the amount of lift a wing is generating as related to weight; ie- amount needed to lift the aircraft. It's expressed in pounds per square foot. Take weight of the aircraft divided by wing area. Direct relation is typically lower wing loading = lower AOA needed to generate particular lift coefficient.
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Hmm so for a given weight the amount of lift needed to support the airplane (wing loading) will increase with a forward CG and decrease with an aft CF, even though weight is consant?
It's the amount of lift a wing is generating as related to weight; ie- amount needed to lift the aircraft. It's expressed in pounds per square foot. Take weight of the aircraft divided by wing area. Direct relation is typically lower wing loading = lower AOA needed to generate particular lift coefficient.
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Hmm so for a given weight the amount of lift needed to support the airplane (wing loading) will increase with a forward CG and decrease with an aft CF, even though weight is consant?
MDPilot
Well-Known Member
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Hmm so for a given weight the amount of lift needed to support the airplane (wing loading) will increase with a forward CG and decrease with an aft CF, even though weight is consant?
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As CG travels forward, more downward "lift" needs to be produced by the tail to keep the nose up and level, adding its downward lift vector to that of weight (1G, level flt assumed) that the main wing has to overcome. Therefore, the need for lift on the main wing increases (by increasing angle of attack, assuming constant airspeed) in order to maintain level flight, and thus the wing loading (lift/sq ft of wing area) increases.
Hmm so for a given weight the amount of lift needed to support the airplane (wing loading) will increase with a forward CG and decrease with an aft CF, even though weight is consant?
[/ QUOTE ]
As CG travels forward, more downward "lift" needs to be produced by the tail to keep the nose up and level, adding its downward lift vector to that of weight (1G, level flt assumed) that the main wing has to overcome. Therefore, the need for lift on the main wing increases (by increasing angle of attack, assuming constant airspeed) in order to maintain level flight, and thus the wing loading (lift/sq ft of wing area) increases.
FlyboyZR1
New Member
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As CG travels forward, more downward "lift" needs to be produced by the tail to keep the nose up and level, adding its downward lift vector to that of weight (1G, level flt assumed) that the main wing has to overcome. Therefore, the need for lift on the main wing increases (by increasing angle of attack, assuming constant airspeed) in order to maintain level flight, and thus the wing loading (lift/sq ft of wing area) increases.
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Ahh now I understand ... I've never thought of tail-downforce as a "weight" ... just a balancing force.
Thanks to the both of you.
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As CG travels forward, more downward "lift" needs to be produced by the tail to keep the nose up and level, adding its downward lift vector to that of weight (1G, level flt assumed) that the main wing has to overcome. Therefore, the need for lift on the main wing increases (by increasing angle of attack, assuming constant airspeed) in order to maintain level flight, and thus the wing loading (lift/sq ft of wing area) increases.
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Ahh now I understand ... I've never thought of tail-downforce as a "weight" ... just a balancing force.
Thanks to the both of you.
