A trajectory-based heating analysis of Galileo probe entry flowfield is attempted to reproduce the heat shield recession data obtained during the entry flight. The mass conservation equations for H2-He mixture and ablation product gas are employed and solved by assuming thermochemical equilibrium. The ablation process is assumed to be quasi-steady and coupled with flowfield calculation. The absorption coefficients of a gas are calculated by multi-band model having 2440 wavelength points. One dimensional radiative transfer calculation using tangent- slab approximation is employed. Park's Injection- induced turbulence model is employed to account for enhanced turbulent effect in the frustum region. The present calculation overestimates heat shield recession for the entire forebody compared with the flight data. However, surface recession histories at the frustum region show fair agreement up to the trajectory point prior to the peak heating point.