DaveD
Well-Known Member
I just want to make sure I'm not missing somthing!
Here are diagrams 10.1 and 10.5 from Peery's Aircraft Structures Book. Fig 10.1 is supposed to show the notional loads on a wing at four "corner" points on the flight envelope (points A,B,C & E on the Vn diagram).
I assumed the arrows in 10.1 were vectors and therefore supposed to have a length that is proportional to loading, but if this is the case they don't look right. The +LAA and -LAA cases have much shorter arrows for the lift vector suggesting that the LAA case is generating smaller lift loads, but if they correspond to point C & E on the Vn diagram (as 10.5 suggests) the loads should be of the same magnitude as the HAA cases. i.e. the aoa will be lower, but because of the increased velocity the forces will be roughly the same magnitude as the HAA case, just located at a different angle and position on the chord.
Am I missing something?
Here are diagrams 10.1 and 10.5 from Peery's Aircraft Structures Book. Fig 10.1 is supposed to show the notional loads on a wing at four "corner" points on the flight envelope (points A,B,C & E on the Vn diagram).
I assumed the arrows in 10.1 were vectors and therefore supposed to have a length that is proportional to loading, but if this is the case they don't look right. The +LAA and -LAA cases have much shorter arrows for the lift vector suggesting that the LAA case is generating smaller lift loads, but if they correspond to point C & E on the Vn diagram (as 10.5 suggests) the loads should be of the same magnitude as the HAA cases. i.e. the aoa will be lower, but because of the increased velocity the forces will be roughly the same magnitude as the HAA case, just located at a different angle and position on the chord.
Am I missing something?
