This study concerns the cryogenic hydrogen combustion in subcritical pressure conditions, with practical relevance to rocket engine applications. A cryogenic two phase flame in the counterflow configuration is calculated and analyzed with the consideration of real fluid effects and heat/mass transfer across the liquid gas interface. The effects of pressure, strain rate, fuel inlet temperature, and heat loss on the flame characteristic behaviors are examined. It is found that the vaporization rate of liquid oxidizer scales with the square root of pressure (p) times strain rate (ast), and is not a limiting factor for combustion. The total heat release scales withffiffiffiffiffiffiffiffip at lower strain rates while with p4=5a1=3 past st at higher strain rates. The significant results on the phase stability of cryogenic flame are also established. It is found that the unstable phase, in terms of vapor liquid equilibrium, arises in the vi cinity of the liquid gas interface; however, all unstable phase states still stay in the metastable region of the phase diagram. For all the flame solutions considered in this study, no thermochemical state enters the spinodal region.(c) 2022 Hydrogen Energy Publications LLC. Published by Elsevier Ltd. All rights reserved.