Valiant
I suspect a misprint in the question.
If the question asked for the load factor increase due to a 2 degree (not 2 percent) increase in AOA then the load factor increase would be 0.079 x 2 divided by 0.35 which is 0.45.
If there is no misprint then there is no need to quote the the change in lift coefficient with respect to one degree of AOA in the first place (it could be a red herring I suppose)
(Don’t worry about the wing being cambered or not as it makes no difference to the method of calculation, which merely relies on the relationship between AOA and Cl being linear – which it will be on a certificated aircraft operating at those sort of Cls ie not at or past the stall. What varies with/without camber is the AOA for a zero Cl This is zero for an uncambered wing and some positive amount for a cambered one- how much positive depending on the amount of camber)
Happy?
JF