1. 126129 'Coupling of Integral 13-134
2. andFinleDaference Techhues Instrumentation 135-137
3. Isolator-Combustor 138-145 TestsandAnalysis 'FreeJet Engine 58, 60.61, 146150
4. Figure 11 shows wall static pressures for a test in a cylindrical duct with an entrance Mach number M, 2.6. Data from other cases are given in Ref. 63. In all cases the static pressure paint plotted at the duct exit station P, is the maximum shock train pressure, whether it he atmospheric or that generated by throttling. The data points for the shock structures originating close to the duct exit represent the lowest value of P,/Pr, inwhich some definition of the shape of the pressure rise could he made (i,e,over a 1-3 in. length). The highest data points correspond to the highest value of P,/P4 in which the shock train could he stabilized in the available duct length. The value of Pw/Pro - 0.34 is somewhat 0.357 -1
5. Pro(Psia)s30.25 - 0