Burning rate plot

Figure 7. Burning rates plotted to test validity of granular diffusion flame...

A typical burning rate plot as obtained from a 107 mg. silica-alumina catalyst particle (commercial type catalyst, 349 m. /g. surface area, as used in Sec. IV.2.c) is shown in Figure 20, from which an oxygen diffusivity of. 0024 cm. Vsec. is obtained. In Table VII a direct comparison is made... 

N.S. Cohen et al, A1AA J 12 (2), 212-18 ( qia QQt 135471 (1974V The effects of inert polymer binder properties on composite solid proplnt burning rate are described. Surface pyrolysis data for many polymers over a wide range of conditions are used to derive kinetics constants from Arrhenius plots and heat of... 

Once ignition has occurred in a mixture of fuel and oxidizer, propagation will continue, provided the concentrations are sufficient and no disturbance results in excessive cooling. The zeroth-order rate model is assumed to represent the lean case. Substituting the selected properties into Equation (4.43), the net release and loss curves are plotted in Figure 4.22 as a function of the flame temperature. The initial temperature of the mixture is 25 °C and fuel mass fractions are 0.05 and 0.03, representative of stoichiometric and the lower limit respectively. At this lower limit, we should see that a steady solution is not possible, and the calculations should bear this out. The burning rate is evaluated at the flame temperature, and 6K is found from Equation (4.44) with Su at the flame temperature... 

Equation (6.179) shows why good straight-line correlations are obtained when Gf is plotted as a function of mo0o for burning rate experiments in which the dynamics of the air are constant or well controlled (i.e 6 is known or constant). One should realize that... 

Fig. 5. Typical rate plots of carbon remaining versus burning time ( ) normal sample (O) initial flattening due to carbon overload (partial inaccessibility). Redrawn from Weisz and Goodwin (1963).

The burning rate of GAP copolymer increases linearly with increasing pressure in an In rversus Inp plot, as shown in Fig. 5.17. The pressure exponent of burning rateat a constant initial temperature, as defined in Eq. (3.71), is 0.44. The temperature sensitivity of burning rate at constant pressure, as defined in Eq. (3.73), is 0.010 K"h... 

Fig. 6.6 shows burning rate characteristics as a function of KNOj). The burning rates are seen to increase linearly with increasing pressure in In r versus In p plots... 

Since the energy density of double-base propellants is directly correlated with KNO2), the burning rates shown in Fig. 6.6 have been plotted as a function of KNO2) at different pressures.h l As shown in Fig. 6.7, the burning rate increases... 

Fig. 6.22 shows a typical set of burning rates for catalyzed and non-catalyzed NC-NG double-base propellants. The burning rate of the non-catalyzed propellant composed of 53 % NC, 40% NG, and 7 % DEP is seen to increase linearly with increasing pres sure in an In r versus In p plot. When the propellant is catalyzed with a com-... 

Various types of binders are used to formulate AP composite propellants. Binders such as HTPB and HTPE decompose endothermically or exothermically at the burning surface. The burning rates of AP composite propellants thus appear to be dependent on the thermochemical properties of the binders used. Figs. 7.17 and 7.18 show In r versus In p plots for AP composite propellants made with five differ-... 

Fig. 7.19 shows the burning rates of AP-HTPB composite propellants at 243 K and 343 K. The propellants are composed of bimodal fine or coarse AP particles. The chemical composihons of the propellants are shown in Table 7.2. The burning rates of both propellants are seen to increase linearly in an In r versus In p plot in the pressure range 1.5-5 MPa, and also increase with increasing initial propellant temperature at constant pressure.Ii l The burning rate increases and the temperature sensitivity decreases with decreasing AP particle size. 

Fig. 7.63 shows plots of In burning rate versus In pressure for AN-(BAMO-AMMO)-HMX propellants with and without (NHJjCrjO and CuCi20. l i The chemical compositions of these propellants are shown in Table 7.8. 

Fig. 15.8 shows a typical set of burning rate versus pressure plots for GAP pyrolants composed of GAP copolymer with and without burning-rate modifiers. The burning rate decreases as the mass fraction of the burning-rate modifier, denoted by (G), is increased. Graphite particles of diameter 0.03 pm are used as the burn-... 

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