Dear fellow PPRuNers,
Would someone be able to give me a leg up regarding the aeroplane mass ratio μ in CS 25.335 (d)(1) (see below)?
K_g = 0.88 μ / (5.3 + μ)
I fully understand that the gust load factor is based on a notional sharp-edged gust, and therefore needs correction for a more realistically shaped gust and load alleviation from the tailplane. Unfortunately, I can't get my head around the rationale behind μ, and the textbooks usually just mention K_g without further explanation.
Any hint would be greatly appreciated.