Total pressure was computed downstream of the nozzle plume and wedge shock interaction, at an axial location of 9.5 inches, or 2 inches downstream of the nozzle

Figure 2.—(a) Three-dimensional axisymmetric CD supersonic “Nozzle 6” from Putnam (Ref. 3), (b) computational domain (centerline cut) for 3-D axisymmetric CD supersonic ‘Nozzle

A wind tunnel test was performed in the NASA Ames 9x7 Supersonic Wind Tunnel focusing on the shock waves traveling through and interacting with an exhaust nozzle plume. The

A high resolution tunable diode laser spectrometer has been installed in the LENS II shock tunnel at CUBRC to study the effect of nozzle exhaust plume interaction with the flow

Refer the Normal Shock tables (Appendix 2). Referring the same following values of  as 2.54. Also there are no losses in the flow, hence the stagnation pressure is also

Curcumin-treated anti-migration and anti-invasion effects was mediated by miR-21 in SU-DHL-8 cells Given the data on cell proliferation and apoptosis, we explored whether

At the nozzle inlet plane for each test case NPR a specified total pressure distribution was applied using the nozzle inlet measurements to include the low total pressure

samples, color indices were to be correlated with government grade, sell-.. ing

A correlation is developed for the SSO distance and pressures uphill distance (PUD) wherein it is hypothesized that the SSO distance is a function of flow Froude

1) Conduct preliminary wind tunnel tests to model a nozzle exhaust jet in ground proximity and study the plume behaviour downstream of the nozzle exit; using

• Demonstrates the feasibility of reducing the magnitude of the sonic boom N-wave by controlling nozzle plume interaction with the boat tail shock structure.... Plume Effects on

Student Success Student Self-Assessment Of General Education Gains 1 Persistence Rate Fall To Fall 1,2 19 Personal/Social Gains 7. 2 Occupational-Technical Degree Satisfaction 3

Interaction between the normal shock wave and the turbulent boundary layer in a supersonic nozzle becomes complex with an increase of a Mach number just before the shock wave1.

However, the CFD shock slopes are found to be smaller than the experimental signature shock slope and slightly shifted to the right (i.e., downstream). Figure 19 shows

showed that miR195 transfection inhibited SW620 cell proliferation, promoted SW620 cell apoptosis, and downregulated Siah-1S level.. Siah-1S overexpression suppressed miR195

Keywords: condensation; water vapor; Laval nozzle; supersonic

Velocity at the inlet of the nozzle is sonic flow, at the throat is sub-sonic flow and at the exit is supersonic flow which is the reason for the shock formation

In this study, the NASA Tetrahedral Unstructured Software System CFD code (USM3D) was used to compute the supersonic nozzle jet flow for two benchmark test cases. For the