I checked all the equations in the Interplanetary How-to-guide and found an error in section 2.
The formula v1 = SQRT((r1*(r2*v22 - 2*μ)+2*r2*μ)/(r1*r2)) has an error.
It should read v1 = SQRT((r1*(r2*v22 - μ)+2*r2*μ)/(r1*r2))
This can be verified by using the deriving formula: v12 = v22 + vesc2 = v22 + (2*μ/r1 - μ/r2) and then reducing to
v1 = SQRT( v22 + 2*μ/r1 - μ/r2 )
Using the same variables names as the guide:
r1 = parking orbit radius
r2 = SOI radius
v1 = ejection velocity
v2 = SOI exit velocity (absolute value)
vesc = escape velocity taking SOI into consideration
This turns out to be a very small correction because r2 is such a large number. Only about 6 m/s in the sample problems.
