It is assumed thai combustion takes place in the turbulent boundary tay,'~ and that the turbuh,tlt ~lante condsts o/ distorted " [letnwl,'ts" but otheru,ts,, vet,tins on a otob'cular scah' the charact~,ristics o/a laminar l~atne. /| /tat-pb~t,' heat-tran,~/rr ~:orv, latton wah a /actor/or truttspiration is u~ed, neglecting toupling ell,'~t.~ o[ the chcnlwal rret~ lion~ in tile tmundat.v layer, The ~lodd equation dcriw'd ff used to ,:ortdatc tbJla avallabb in the, tit,'raturc [.r erosive burning, ihe ~,qt.ation ~s ]ovnd to b; applicabl., for a 'hhm,'int./ /a~lor, L#~/G ~ 0.02 t. 11.03. It is coniiudΒ’ ,d, t~.ntut.vcly, that th; tontΒ’.lhng ,B, tnt(af v, actvm ~ #rs1-order, possib.'v th,, gu.~-phas," d,.compa~itmll o/ p,~chl.t~, arm .r .] the ~omplca f SIl:~ β’ IlrlO. Notadon a. b Proportionality constants B Thermrgiynamie mass transfer nlllllher C Specific heat G Local mass flux G*. Local cdtical mass flux h Convective heat transfer coefl~ci~.nt with transpiration Convective heat transfer coefficient without transpiration kt, kv k=, k' Proportionality constants l Thickness of flame Mass burning rate Mg Moletuhr weight of combustion gases n' Burn rate pressure exponent ~" Order of chemical kinetics ~p Average partial pressure Local static pressure Pr Prandtinumber Q, Net heat release for propellant gasi-~ation R Gas constant r, Propellant linear burn rate T Temperature ta Time for chemical reaction of unit mass t,,o... Time for turbulent transport per unit mass V Local gas velocity F, Flame volume X I)i.,t;tm'v fl,ttJt head eml ,)fdl,' l)rW wlhmt ~rain z 'lJll, witjg ' rail-, v,p. : Β’; 1} J.q'.j)vll;mt ce)flstatlt 7 N)t'cifi,' hval I';tli,~ A, A' TJ|(,rl~la] coltdllctivil V, tllrth,,Clll;lf ;ll|d {~ddy wspt'i:ti','~'ly /at (;aS vlsco~ity V', 1~'Β’ StoichJorl|etric c.(.llicie[li', ,xi,lizer itlld tllel ri.sl~.ctiv,,ly p. J~r,q.'llam (h.tl~ity T T.ta] tif}h' io bllHi qnit m;x~ ,Jr prtqJ~llant Sttbscripts s S,lid g.. Gas ; Initial o ];ore-or h('i](i.erld ,t rocket