Development of a procedure to model the hot shape of a rotor blade and a comparison analysis of the transonic axial splittered rotor (TASR), tandem stator (TS) stage has been investigated. The ability to implement this procedure into the current Naval Postgraduate School (NPS) Turbo propulsion Lab (TPL)design procedure that uses commercial off the shelf software has been documented. The TS stage was tested at multiple clocking positions over the full speed range of the rotor. The best performance was observed at a negative 10 percent clocking position relative to the design configuration. Numerical simulations were conducted of both hot and cold rotor shapes and compared. This study advanced the understanding of simulating the hot shape of a rotor to better match the results of experimental data. The hot shape results closely resembled that of the cold shape results; however, the hot shape achieved a greater mass flow range. The procedure developed is easily implemented, utilizing a fluid-structure interaction. Rotational forces as well as gas loading forces were observed as an influence on blade deformation. Utilizing the procedure to model the hot shape of the rotor will be essential in deriving numerical results for a comparative analysis.