VA = VS1 x sq.rt. (Max load factor)
where VA = manoeuvring speed
and VS1 = stalling speed in the configuration being examined (typically, nil flap, wheels up if applicable)
and max load factor is the limit (or maximum permitted) load factor in the configuration being examined.
This is not entirely accurate as VA is based on many variables not just positive load factor. However, it gives a good rule of thumb.
Note that a) it only addresses positive load factor, not negative and b) it does not guarantee protection in all circumstances. For example "rolling g" refers to the simultaneous application of full aileron and full up elevator - manufacturers are only required to protect to two thirds limit load factor in this case for many aircraft. Refer FAR or JAR Part 23.
Hope this helps as an intro to the subject,
Oktas8