The electron sheath structure around a cylindrical body with a finite length that is biased to a high positive potential in a magnetized nonflowing ionospheric plasma with enhanced neutral density is studied. The results of Monte-Carlo particle-in-cell simulations show that the sheath boundary increases as the neutral density increases and ionization occurs inside the sheath. There is a critical neutral density above which the sheath expands infinitely, i.e., sheath explosion. A formula of the critical neutral density is derived through theoretical formulation. The theoretical results are compared with the results of the simulation, which serves as a numerical experiment, to check the validity of various assumptions made to derive a simple formula for the critical neutral density. The theoretical formula predicts that the critical neutral density lies in a narrow range of 6 x 10 16 ~ 6 X 10 17 m~3, leaving little dependence on the spacecraft surface potential at typical ionospheric conditions. Nomenclature a = nondimensional parameter,. B= magnetic field strength, G b = nondimensional parameter, a) ce /co pe c = nondimensional parameter, Ej/e^p Ej = threshold value of impact energy for ionization collision rate to be nonzero, eV I eo = total electron current to upper half body of spacecraft, A L = axial half length of trapped zone, m L c = axial half length of spacecraft, m m = particle mass, kg n = particle number density, m~3 n nc = critical neutral density, m~3 q = charge of one superparticle r c = electron collection radius, m r/ = ionization radius, m r L = radial boundary position, m r PM = Parker-Murphy radius, m r p = spacecraft body radius, m r. v = sheath boundary radius, m T eo = ambient electron temperature, K v 0 = electron thermal flux velocity, m/s v rs i = secondary ion radial velocity, m/s w = nondimensional ionization radius, r//r p x = nondimensional sheath radius, r s /r p y -nondimensional collection radius, r c /r p ZL = axial boundary position, m r er -electron radial flux, l/m 2 /s P ez = electron axial flux, l/m 2 /s Xj = debye length, m v es = effective scattering frequency, s" 1 erf = ionization collision cross section, m 2 (criV e ) = ionization collision rate averaged over electron velocity distribution function, m 3 s" 1 0 = electric potential, V (j) p = spacecraft body surface potential, V ct) ce = electron gyrofrequency, rad/s o) pe = electron plasma frequency, rad/s n si = neutral = secondary ionSubscripts ai e = ambient ion = electron