Abstract
This paper presents theoretical and experimental results for estimating electromagnetic wave attenuations caused by the presence of rocket exhaust plumes with afterburning in the propaga- tion medium between a ground station and a rocket-powered vehicle.
The approximate distributions of the velocity, temperature and concentration of the rocketplume are obtained in the analytical forms by solving the boundary layer equations under some assumptions.
The distributions of the rocket composite propellant are presented in graphical form. Wave propagation characteristics passing through a flame with the high collision frequency compared to the frequency used for flame diagnostics are discussed.
The predicted and experimental wave attenuations along the nozzle center axis are compared with qualitatively good agseement.
