A power plant continuously releases from a 70-m stack a plume into the ambient atmosphere of temperature 298 k. The stack has a diameter 5m, the exit velocity is 25 m s^-1, and the exit temperature is 398 K. For neutral conditions and a 20 km h^-1 wind, how high above the stack is the plume 200 m downwind?

A power plant continuously releases from a 70-m stack a plume into the ambient atmosphere of temperature 298 k. The stack has a diameter 5m, the exit velocity is 25 m s^-1, and the exit temperature is 398 K. For neutral conditions and a 20 km h^-1 wind, how high above the stack is the plume 200 m downwind?

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.29P: Air at 20C flows at 1 m/s between two parallel flat plates spaced 5 cm apart. Estimate the distance...

See similar textbooks

Similar questions

Water at 20 ° C fl ows through a long elliptical duct 30 cmwide and 22 cm high. What average velocity, in m/s, wouldcause the weight fl ow to be 500 lbf/s?
Consider the Gulfstream IV flying at Mach = 0.35. Calculate thrust required given an altitude of 30,000-ft, assuming weight of 73,000-lb. Airplane data: S = 950 ft2, AR = 5.92, ??? = 0.015, and K = 0.08 a. The thrust required at 30,000-ft. (in pounds)
Consider a flow of SAE 30W oil through a 3-cm-diameter pipe. For SAE 30W oil, take ρ = 891kg/m3, μ = 0.29 kg/m⋅s at 20 °C, and μ = 0.01 kg/m-s at 100 °C, and π = 22/7. For what flow rate in m3/h would a transition to turbulence take place at 20°C? The flow rate is m3/h.
Suppose a gas flows through a constant insulated path. Parameters of temperature, pressure and mach is 520R, 50psi and 0.45 respectively. A point in the downstream calculated the mach number to equal to 1. Calculate for the temperature and pressure downstream. Methane Gas (k=1.32, R=96.4 ft-lbf/ lbm-R) 1 slug = 32.174 lbm
Water at 20 ° C fl ows through the elbow in Fig. P3.60 andexits to the atmosphere. The pipe diameter is D 1 = 10 cm,while D 2 = 3 cm. At a weight fl ow rate of 150 N/s, thepressure p 1 = 2.3 atm (gage). Neglecting the weight ofwater and elbow, estimate the force on the fl ange bolts atsection 1.
a) Estimate the drag force on the plate. You may use the expression ?? = ∫ τ?d? b) When the flow becomes turbulent, we can approximate the velocity gradient at the wall as constant, ∂? ∂? = ?. If the total drag force is 300 N, find ?. c) When the fluid is heated to 90oC, the density drops slightly and the viscosity decreases a lot, and engineers observe that the equation, τ? = 0.0644??∞ 2 δ ? , becomes less accurate. Explain why this might occur (1-2 sentences)
A water jet 7.6 cm diameter strikes concrete (SG=2.3) slab which rests freely on a lever floor. If the slab is 30.5 cm wide into a paper, calculate the jet velocity which will just begin to tip the slab over.
The small boat in Fig. P3.48 is driven at a steady speed V 0by a jet of compressed air issuing from a 3-cm-diameterhole at V e = 343 m/s. Jet exit conditions are p e = 1 atm andT e = 30 ° C. Air drag is negligible, and the hull drag is kV0 2 ,where k ≈ 19 N ? s 2 /m 2 . Estimate the boat speed V 0 in m/s.
A Kelvin oval is formed by a line–vortex pair with K =9 m2/s, a = 1 m, and U =10 m/s. What are the height,width, and shoulder velocity of this oval?
Assume an inviscid, incompressible flow. Also, standard sea level density and pressure are 1.23 kg/m3 (0.002377 slug/ft3) and 1.01 × 105 N/m2 (2116 lb/ft2), respectively. Consider a low-speed open-circuit subsonic wind tunnel with aninlet-to-throat area ratio of 12. The tunnel is turned on, and the pressuredifference between the inlet (the settling chamber) and the test section isread as a height difference of 10 cm on a U-tube mercury manometer.(The density of liquid mercury is 1.36 × 104 kg/m3.) Calculate thevelocity of the air in the test section.
When an oblique shock strikes a solid wall, it reflects as ashock of sufficient strength to cause the exit flow Ma3 to beparallel to the wall, as in Fig. For airflow with Ma1 =2.5 and p1 = 100 kPa, compute Ma3, p3, and the angle ϕ.
Find the minimum engine thrust that is required for a business jet to maintain level flight at standard sea level conditions.weight, W = 20,000 lb; wingspan, b = 54 ft; wing area, S = 320 ft2zero-lift drag coefficient, CD0 = 0.023aerodynamic efficiency factor, e = 0.82Answer: thrust required = ______________ [lbf]