The rocket performance of liquid silanes with highly concentrated H 2O2 as rocker bipropellants using the new thermodynamic data was investigated. The vacuum-specific impulses, combustion temperatures in the chamber, nozzle expansion ratio, and densities of the fuels are given as well as the equivalence and corresponding oxidizer-fuel-mass ratio that would be used to obtain the maximum specific impulse. Non toxic hypergolic miscible fuels (NHMF) have been developed that allows to obtain up to 93% of the specific impulse of the NTO/MMH when used with 98% grade H2O2. The ideal rocket performance of the combination of silicon hydrides and 98% pure H2O was predicted to be higher than NTO/MMH at the same conditions. All the silanes/RGHP (rocket-grade hydrogen peroxide) yielded a better peak Ivac and the vacuum-specific impulse of SiH4/RGHP is 10% higher than for NTO/MMH.