This work emphasizes the need to have an in-depth understanding of the attenuation suffered during the propagation of microwaves through solid rocket motor (SRM) exhaust plume. Rocket motor exhaust plume is characterized as weakly ionized plasma. Two important parameters are involved in numerically modeling the plasma; the electron collision frequency and plasma pulsation frequency. Literature survey showed that from an exact assessment of attenuation at two or three microwave frequencies, which are sufficiently spaced apart, it is possible to predict the attenuation at any other frequency of interest. An experimental setup to study the attenuation in C band is described in this paper. The initial test results obtained with certain mounting condition of antennas with respect to exhaust jet is presented in the paper. Experiments were conducted at 5.6 GHz transmit frequency, which is of interest to rocketry and space communications. As a parametric variation, the transmission frequency was increased by 400 MHz and few test cases were also carried out. The variation of attenuation with respect to the positioning distance of the transmitter–receiver pair from the nozzle exit is presented. The shortcomings of the subscale motor level experiments and the improvements that are required are also described.