Alternatively, does anyone know it?
I'm asking in regards to the upcoming DSCOVR (Deep Space Climate Observatory) mission scheduled to launch aboard a Falcon 9 v1.1 rocket in January 2015. DSCOVR is 507 kg in mass and will be headed to the Sun-Earth L1 (SEL1).
I'm trying to calculate the payload fraction of the rocket based off the C3 (characteristic energy) involved. I'm assuming it'll be greater than 0 km2/s2 and less than 12.2 km2/s2, which is the C3 of MAVEN to Mars.