PROTRACED COUNTERINSURGENCY: CHINESE COIN STRATEGY IN XINJIANG by MAJ J. Scott LaRonde, USA, 95 pages. In 1949, following the conclusion of its revolutionary war against the Chinese Nationalist forces, the People’s Liberation Army (PLA) peacefully occupied China’s western most province of Xinjiang. For nearly sixty years, the PLA has conducted a counterinsurgency against several, mostly Uyghur-led, separatist movements. Despite periods of significant violence, particularly in the early 1950s and again in the 1990s, the separatist forces have not gained momentum and remained at a level one insurgency. Mao ZeDeng is revered as a master insurgent and the father of Fourth Generation Warfare. Strategists in armies worldwide study his writings on revolutionary and guerilla warfare. This monograph concludes that Mao, as well as the communist leaders who followed him, was also successful at waging protracted counterinsurgency. For nearly sixty years, separatist movements in Xinjiang, Tibet, and Taiwan have all failed. This monograph analyzes the conflict in Xinjiang and concludes that the Chinese continue to defeat the separatist movement in Xinjiang through a strategy that counters Mao’s seven fundamentals of revolutionary warfare.

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Approved for Public Release; Distribution is Unlimited

Analyse theorique de l'ecoulement dans des tubes et canaux a paroi poreuse. On tient compte des effets de compressibilite, de conditions aux limites non ideales et de transition turbulente sur le developpement de l'ecoulement. On utilise un modele de turbulence a contrainte de Reynolds et un schema de differences finies implicite pour resoudre le systeme d'equations paraboliques resultant

Injection-induced flows in porous-walled ducts

An analysis of the vapor flow and the heat conduction through the liquid-wick and pipe wall in a heat pipe with single or multiple heat sources

A numerical analysis has been performed to study cold flows in a nozzleless solid-rocket motor (SRM) consisting of a two-dimensional porous-walled duct and an impermeable-w alled diverging expansion section. The finite volume technique was used to solve the Navier-Stokes equations without subgrid-scale turbulence models, and the numerical fluxes were computed using a modified Godunov's scheme. Computed results are compared with existing experimental data, including mean pressure and axial velocity, the transition process of the meanvelocity profile, the level and shift of the turbulence intensity peak, and the pressure contour near the diverging expansion region. Furthermore, this study addresses the effects of wall injection on the near-wall velocity profiles of the fully turbulent flat-plate flow and the validity of the "law of the wall" throughout the flowfield in an SRM. B+ = Cf = e = F = G = h = / = /,, = k =

Numerical Simulations of Injection-Driven Flows in a Two-Dimensional Nozzleless Solid-Rocket Motor

A theoretical analysis to determine the effects of mass addition on the inviscid but rotational and compressible flowfield in a porous duct with the injection rate dependent on the local pressure is performed for large ratios of length-to-duc t diameter. The problem of describing the flow is reduced to the solution of a single integral equation. The ratio of specific heat 7, and a constant pressure exponent u, measuring the dependence of the rate of mass injection on the local pressure, are the parameters of the solutions. The integral equation is solved numerically, and parametric results are presented for 7, varying from 1 to f and for n varying from 0 to 1. A choking phenomenon is exhibited at a critical length of the duct in the vicinity of which the Mach number approaches unity. The choking condition, which is relevant to the operation of nozzleless solid-propellant rocket motors, is obtained parametrically in the present study and compared with corresponding results for irrotational, quasi-one-dimensional flow. The rotationality reduces the choking pressure. Nomenclature A = cross-sectional area of the duct a = radius of the duct C = average speed-of-sound in the fluid cp = the specific heat of the fluid at constant pressure h = half-height of channel 7sp = specific impulse of the motor K = constant prefactor in the burning-rate law for the propellant / = length of the duct M = Mach number m = mass burning rate of the propellant n = pressure exponent in the burning-rate law for the propellant P = nondimensional pressure p/pQ p = dimensional pressure R - ratio of the specific impulse obtained by assuming quasi-one-dimensional flow to the specific impulse obtained by assuming rotational flow r = dimensional radial coordinate 5 = perimeter of the duct T - temperature t = time u = axial component of the velocity Vw = injection velocity v = radial component of the velocity X — nondimensional axial strained coordinate defined in Eq. (23) x = dimensional axial coordinate y = distance normal to.the propellant surface y = ratio of specific heat A =. boundary-layer thickness 8 = gas-phase flame standoff distance 17 = dimensional transverse coordinate in channel flow p pp = gas density = propellant density = function related to entropy

Rotational inviscid flow in laterally burning solid-propellant rocket motors

Vapor Flow in Cylindrical Heat Pipes

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Vapor Flow in Cylindrical Heat Pipes