RS-25 (SSME) vs RD-0120 efficiency

[jurgennasaspaceflight]

What if RS-25 (SSME) and RD-0120 had the same thrust and weight hypothetically, which one would have been more efficient based on their specific impulse?
Isp for RS-25 (SSME) is 366s sea level 452.3s vacuum
Isp for RD-0120 is 354s sea level 455s vacuum

[Hog]

First of all, welcome to NASA Space Flight.com.

Second, your question. 
Assuming test stand conditions:
engine mass doesn't matter
The engine with greater Isp would be the more efficient engine because Specific Impulse is actually ""a measure of how efficiently a reaction mass engine, such as a rocket using propellant generates thrust. ""  source:Wiki's Specific Impulse page.
In summation, assuming your numbers are correct, it appears that the RS-25 is more efficient than the RD-0120 down at Sea Level whilst the RD-0120 is more efficient than the RS-25 when operating in vacuum.

attachment
1) just a slide with some modern RS-25D Isp, thrust, service life as used for STS and for SLS Adaptation and Restart engines