Satellites that would operate in Very Low Earth Orbit (VLEO) offer significant advantages such as improved resolution for imaging and lower latency for communications. To take advantage of these benefits, the Institute of Space Systems (IRS) at the University of Stuttgart is developing the Atmosphere-Breathing Electric Propulsion (ABEP) system. This innovative propulsion method utilizes atmospheric particles for drag compensation, potentially extending mission lifetimes in VLEO. The ABEP system, with its electrodeless design concept, addresses erosive effects caused by atomic oxygen in the atmosphere on propulsion system components, enhancing their durability. Under this initiative, the RF Helicon-based Inductive Plasma Thruster (IPT), developed within the EU DISCOVERER project, serves as a laboratory model for thruster investigation and is planned to be a particle flow generator for VLEO conditions. This thesis focuses on the plasma plume characterization of IPT, including measurements of thrust, pressure, and particle composition measurements to define flow characteristics. Furthermore, the feasibility of the Pitot probe was assessed, determining that the IPT likely operates in a rarefied flow regime, specifically in a transitional flow regime, due to its low temperature and pressure. Additionally, pressure values were estimated from momentum flux measurements, which showed that plasma properties such as density, temperature, and pressure were affected by variations in RF power, reflected power, mass flow rate, and solenoid current. Additionally, Optical Emission Spectroscopy (OES) analysis revealed that the plasma plume from IPT was most likely operating in an inductively coupled plasma mode since only Ar I emission spectral lines were dominant in the spectra.