A one-dimensional flow model of the chemical laser, from combustor to subsonic diffuser, is developed for the study of laser pressure recovery. Combustor and flow chemistry effects, nozzle and cavity boundary-layer losses, laser cavity combustion, and nozzle, cavity, and diffuser geometry influences are included in the analysis. The results from experimental tests on a laser nozzle array with a constant area diffuser are presented. Diffuser exit pressures as high as 263 Torr were measured during these experiments. The one-dimensional flow model is shown to be in agreement with the measured diffuser exit pressures over the full range of test conditions.
A AR C D Hpp Nomenclature = area = nozzle area ratio =yth station molar heat capcity, 2J XjiC pi -cavity exit hydraulic diameter = ith specie heat of formation =yth station sensible enthalpy, 2y \ C pi dT =yth station stagnation enthalpy, h } + 1/2 M wj U 2 j =yth station enthalpy, H 0j ; + £j X^hî =yth station total enthalpy, nfij = mass flow = Mach number, U/(yRT) l/2 =yth stream molecular weight,2j XjiM wi -molar flow ' = fluorine available in cavity as F 2 , 1/2 n p ? + n p¥l = pressure = cavity heat release = normalized heat release, Q/n p p 2 = gas constant = cavity mixture ratio, n sr>2 /n p p 2 = temperature = velocity = mole fraction, /i_////i/; X p = n p /n 3 , X s = n s /n 3 = mass fraction, myjmj -fluorine dissociation, 1/2 n pP /n p p 2 = deuterium dissociation, n 4D /n pF = specific heat ratio = laser specific power, (9^/m 3 =yth stream dilution level,^ ^/ 5 T = secondary, fuel stream = second throat diffuser m M M n n P Q q R R L T U y a \l/j Subscripts 0= stagnation state 1-7 = flow stations; Fig. 1