guys....
with regard to the question on stall speed,
the formula for lift is : LIFT= (C.L) * {(0.5) * (rho) * (TAS) * (TAS)}
where {(0.5) * (rho) * (TAS) * (TAS)} is the dynamic pressure, which gives the indicated airspeed.
So, from the above equation, when we equate for {(0.5) * (rho) * (TAS) * (TAS)} , it will be : (dynamic pressure) = LIFT/(C.L)
and stall occurs when the coefficient of lift is maximum.
Hence, during stall, (dynamic pressure) =LIFT / (C.L max)
and since C.L max is constant for an aerofoil and the load factor is directly proportional to the Lift produced during straight and level flight, if the load factor acting on an A/c is the same, it will always stall at the same IAS.
Also, when (C.L) = (C.L max) , that is the AoA at which the A/c will always stall irrespective of the Altitude or the speed. { Please note that whenever most of the books say speed, they mean the TAS (v) }
Now , from the very first equation , if we equate for the speed {i.e TAS (v)}, we get
(TAS) * (TAS) {or (v squared)} = [ LIFT / { (C.L max) * (0.5) * (rho) }]
hence TAS {or (v)} will be equal to the square root of the expression on the right hand side of the above equation.
From the derived equations for the TAS {or (v)} and the IAS , we see that density (rho) is involved only in the equation,
So.... Under constant load factor, the IAS at which an A/c will stall will always remain constant, but the TAS will vary inversely with density
i.e , the A/c will stall at a higher TAS at higher altitudes, since density is lower.
Hope this helps .
Best o Luck to all u guys....
