Over a 30 m length of 150 mm vacuum line carrying air at 293 K (Molecular Weight =26.44 kg/kmol, Viscosity = 18.12*10^-6 N s/m^2), the pressure falls from 1 kN/m^2 to 0.1 kN/m^2. If the relative roughness e/d is 0.002, what is the approximate mass flow rate? (unit is required).

ES Font English (United Kingdom) ▬▬ Q Search > Text Predictions: On ALT Paragraph S Accessibility: Good to go Styles The following parameters characterise a liquid-fuelled rocket engine: stagnation pressure P0=100bar; stagnation temperature TO=3300K; nozzle exit diameter DE=1.0m; throat diameter=0.1 m; gas constant R=692 Jkg-1 K -1; ratio of specific heats cp/cV=y=1.25. Estimate the following: static pressure at the exit plane, exit Mach number. Heading Focus Editing ENG UK

Py Flow FIGURE 6.2 Portion of a fluid distribution system showing variations in velocity, pressure, and elevation. Reference level 2.