The laminar combustion characteristics of surrogate fuel for RP-3 aviation kerosene were investigated experimentally in a constant volume bomb. The experiments were performed at initial pressures of 0.1

0.3 MPa

initial temperatures of 390

400

420 K

and over the equivalence ratio range of 0.8-1.5. Furthermore

the laminar combustion velocities of the surrogate fuel and RP-3 aviation kerosene were contrastively analyzed. Results showed that decreasing the initial pressure or equivalence ratio increased the stability of the flame front

which was established by increased Markstein length. The effect of the initial temperature on the Markstein length was not clear. Increasing the initial temperature or decreasing the initial pressure led to an increase in the laminar combustion velocity of the surrogate fuel. With the increase of equivalence ratio

the laminar combustion velocity illustrated an increase initially and then decreased gradually

and the highest value was measured at the equivalence ratio was 1.2. Furthermore

the laminar combustion velocity of the surrogate fuel agreed well with that of RP-3 aviation kerosene under the same conditions.