# How to find the transfer orbit from a initial circular orbit to a final elliptical orbit

Is a hohmann transfer or bi-elliptical transfer more efficient for this case? How can I find the transfer orbit that conserves the most deltaV?

I will be going from a circular Earth centered orbit to an elliptical sun centered orbit. Assuming the orbits are coplanar.

• Neither Hohmann or bi-elliptical transfers are appropriate. This would be a bi-tangential transfer, where the first burn is complicated by also being an escape from Earth. – JCRM May 11 at 11:03
• I found other posts on this cite about the bi-tangential orbit but wasnt sure about the deltaV that will be needed for the maneuver – Freddy May 12 at 2:37

The semi-major axis and eccentricity of your target orbit will determine whether a Hohmann transfer (i.e. bi-impulse transfer) or bi-elliptic transfer (i.e. tri-impulse transfer) is more $$\Delta$$V efficient.