much smaller coil significantly more effective. The pressure of the inflated plasma along with the stronger magnetic field pressure at a larger distance due to the lower falloff rate would stretch the magnetic field and inflate a magnetospheric bubble around the spacecraft. The 2000 Winglee paper described a design and reported results adapted from the Earth's magnetosphere. Parameters for the coil and solenoid were =2.5 cm and for the coil = 0.1 m, 6 orders of magnitude less than the magsail coil with correspondingly much lower mass. An estimate for the weight of the coil was 10 kg and 40 kg for the plasma injection source and other infrastructure. Reported results from Figure 2 were T at 10 km and from Figure 3 an extrapolated result with a plasma injection jet force 10−3 N resulting in a thrust force of 1 N. The magnetic-only sail force from equation is =3x10−11 N and thus M2P2 reported a thrust gain of 4x1010. Since M2P2 injects ionized gas at a rate of (kg/s) that can be viewed as a propellant it has a specific impulse where (m/s2) is the acceleration of Earth's gravity. Winglee stated =0.5 (kg/day) and therefore =17,621. The equivalent exhaust velocity is 173 km/s for 1 N of thrust force. Winglee assumed total propellant mass of 30 kg and therefore propellant would run out in 60 days. In 2003, Khazanov published MagnetoHydroDynamic (MHD) and kinetic studies that confirmed some aspects of M2P2 but raised issues that the sail size was too small, and that very small thrust would result and also concluded that the hypothesized magnetic field falloff rate was closer to . The plasma density plots from Khazanov indicated a relatively high density inside the magnetospheric bubble as compared with the external solar wind region that differed significantly from those published by Winglee where the density inside the magnetospheric bubble was much less than outside in the external solar wind region. A detailed analysis by Toivanen and others in 2004 compared a theoretical model of Magsail, dubbed Plasma-free Magnetospheric Propulsion (PFMP) versus M2P2 and concluded that the thrust force predicted by Winglee and others was over ten orders of magnitude optimistic since the majority of the solar wind momentum was delivered to the magnetotail and current leakages through the magnetopause and not to the spacecraft. Their comments also indicated that the magnetic field lines may not close near enough