Abstract: In terms of the mission analysis of spacecraft re-entering to the earth's surface from the outerspace in orbit, it is presented that the designs of the aerodynamic configuration on the spacecraft re-entry module need both to be optimized to meet the requirement of re-entering performance, the constraints of the spacecraft, and the requirements of loading mission. From the point of view of case analysis, the overall design ideas for determining the configuration of various typical re-entering spacecraft are systematically expounded. On the basis of researching, it is elaborated that the requirements of flight dynamics and thermodynamic parameters affect the aerodynamic shape, and it is shown that the ratio of lift and drag and the local thermal environment are the key parameters for the aerodynamic configuration of the spacecraft. By the classification of the aerodynamic shape on spacecraft re-entry module, the characteristics of various types of performance, and the application of the situation have been sorted out. It is proposed that the simple body shape is the amature, economical, safe and reliable way to complete the task of re-entry from outerspace to earth. The lift-body configuration is an other option for low cost and high re-entry flight performance. Based on taking the aerodynamic shape of a spaceship's re-entry module as the researching object, the requirement and necessity in developing the numerical methods for the aerodynamics covering various flow regimes has been presented by the results analyses of the gas-kinetic unified algorithm in solving the Boltzmann model equation, DSMC, N-S/DSMC and N-S solver, and the validation with the flight test data for the near-continuum transitional flows.