Accession Number : AD0718776

Title :   Transient Subsonic Viscous Flow in the Vacuum-Air Propulsion System.

Descriptive Note : Interim technical rept. no. 5,

Corporate Author : ARMY RESEARCH OFFICE DURHAM N C

Personal Author(s) : Rajan,Jai R. N. ; Kumar,Sudhir

Report Date : SEP 1966

Pagination or Media Count : 230

Abstract : A general discussion of the vacuum-air propulsion system and its historic development and a nonsteady analysis of this system, which includes the losses due to viscous friction, inertial and acceleration effects besides other losses is given. This analysis consists in the simultaneous solution of the equation of motion of the projectile and construction of the characteristic net with the aid of a digital computer. A nonsteady isentropic analysis is also developed prior to the viscous flow analysis. Experimental studies were conducted with two models: (1) A 105 ft long, 6 in. I. D. tube with projectiles of weights from 0.62 lb to 11.52 lb; (2) An 85 ft long, 2 in. I.D. tube with projectile weights from 0.033 lb to 1.7 lb. Highest projectile velocities recorded were 1145 ft/sec. Predictions of projectile velocity, entrance flow velocity and pressures behind and ahead of the vehicle made by the nonsteady viscous flow analysis agree well with experimental data. (Author)

Descriptors :   (*GUIDED MISSILE LAUNCHERS, *VACUUM), (*PASSENGER VEHICLES, PROPULSION SYSTEMS), EQUATIONS OF MOTION, SUBSONIC FLOW, SKIN FRICTION, MODEL TESTS, VELOCITY

Subject Categories : Surface Transportation and Equipment
      Guided Missile Launching and Basing Support

Distribution Statement : APPROVED FOR PUBLIC RELEASE