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A quasi-steady compressible flow analysis of the vacuum-air missile boost-system is presented. Also an improved incompressible flow analysis which includes the effects of internal pressure loss and entrance loss. Experiments on a 101 ft. long 6 in. 1D tube model, for launching projectiles of weights from 11.52 lbs. to 1.50 lbs were conducted. Terminal velocities between 300 and 950 ft/sec. were recorded. Agreement between the theoretical predictions made by the cmpressible flow analysis and the experimental results was quite good for velocities up to 850 ft/sec. For higher velocities the theory predicted smaller velocities than those recorded, and transient wave analysis is considered desirable. (Author), See also Interim technical rept. no. 5, AD-718 776. Report on Project Mountainwell. Master's thesis submitted to Duke Univ., Durham, N. C., Dept. of Civil Engineering.