by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, DC, [Springfield, Va .
Written in English
|Statement||by G.S. Liaw and J.D. Mo.|
|Series||NASA contractor report -- NASA CR-189533.|
|Contributions||Mo, J. D., United States. National Aeronautics and Space Administration.|
|The Physical Object|
low thrust viscous nozzle flow fields prediction grant na (first year report) submitted to national aeronautics and space administration marshall space flight center (nasa-cp) low thrust viscous nozzle n flow fields prediction annual report rio. 1, • ;alabama a 6 m (iniv.) 34 p. A Navier-Stokes code was developed for low thrust viscous nozzle flow field prediction. An implicit finite volume in an arbitrary curvilinear coordinate system lower-upper (LU) scheme is used to solve the governing Navier-Stokes equations and species transportation : G. S. Liaw and J. D. Mo. The low thrust viscous nozzle flows have been studied numerically by using the steady-state Reynolds-averaged Navier-Stokes equations in conservative form. A new Lower-Upper factorization scheme in the axisymmetric coordinate system has been developed and is analyzed in this : L. C. Chou, J. D. Mo and G. S. Liaw. For such small, low-thrust nozzles, the boundary layer can account for a sub- stantial portion of the available nozzle flow area. The boundary layer introduces viscous losses and alters the free-stream conditions so that the conventional assumption of a one- dimensional isentropic expansion process becomes questionable. The nozzle flow is fur-Cited by: 8.
subsonic flow during this section will simply be turned at terribly low drop and any radius. Nozzles have a viscous physical phenomenon next to the walls, wherever the gas velocities area unit a lot of under the free stream velocities within the in gummy flow regions. The gaseous physicalFile Size: KB. The investigated low-Reynolds-number, quasi-laminar range permits highly resolved simulation of the inner-nozzle flow. Outside the nozzle, a geometric VOF method is utilized for resolving the sharp liquid-gas interface. The governing equations are solved in the open source fluid dynamics library OpenFOAM (Weller et al., ). First, Eq. Find the nozzle requirements for a given pressure or flow rate. Learn more about the units used on this page. This form is used to calculate the flow rate of a nozzle given the pressure. This form is used to calculate the needed diameter of a nozzle for a specific pressure and flow rate. This calculator uses this formula to determine the Flow. The cause of low-cycle fatigue failure of the K Thrust Chamber was investigated. This thrust chamber typifies the current trend in rocket nozzle design which calls for high performance coupled with weight and volume limitations as well as the requirement of reusability.
Get this from a library! Low thrust viscous nozzle flow fields prediction: final report. [G S Liaw; J D Mo; United States. National Aeronautics and Space Administration.]. Computation of Two-Dimensional, Viscous Nozzle Flow. Michael C. Cline ; Michael C. Cline. University of California, Los Alamos, New Mex. Experimental and numerical investigations of low-density nozzle and plume flows of nitrogen. A computational analysis of the transonic flow field of two-dimensional minimum length by: The accurate numerical prediction of gas flows within micro-nozzles can help evaluate the performance and enable the design of optimal configurations for micro-propulsion systems. Viscous effects within the large boundary layers can have a strong impact on the nozzle performance. Furthermore, the variation in collision length scales from continuum to rarefied preclude the use of Author: Timothy R. Deschenes, Jonathan Grot. Experimental investigation of the effect of extended cowl on the flow field of planar plug nozzles. Aerospace Science and Technology, Vol. 88 Numerical study of low-thrust nozzles for satellites. Spike nozzle contour for optimum thrust. Planetary and Space Science, Vol. 4. Book Cited by: