Calculating IAS from lift equation
Hi,
Given Cl = 0.2, Weight of aircraft = 170 tonnes and Smainwing = 250m^2 and Stailwing = 56m^2 is it possible to calculate the IAS (in km/hr) the aircraft should travel so that L = W ?
I am really struggling to work this out - the numbers I am coming up with just don't make sense, so if anyone out there could help me out it would be greatly appreciated!
Thanks in advance!