Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
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Chapter 8, Problem 8.3P
At a given point in a flow,
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At a given point in a flow, T = 300 K, p = 1.2 atm, and V = 250 m/s. Atthis point, calculate the corresponding values of p0, T0, p∗, T ∗, and M∗.
Methane in the gaseous state flows at a rate of 0.072 m^3/s in a pipe at a
temperature of 27°C and gauge pressure of 148.675kPa (point 1). The pipe is
divided into two branches (point 2 and 3), as seen in the figure. If the exit
velocity in pipe 3 is 12 m/s with a density of 1.9 kg/m^3, what is the flow rate and
velocity in pipe 2? Consider that in section 2 the fluid is leaving with a
temperature of 402°C and an absolute pressure of 175 kPa. We have an
atmospheric pressure of 101.325 kPa and R_methane = 0.5182 kJ/kg ⚫K.
(1)
Inflow
D1
D3=50mm
D2=100mm
(3)
(2)
R₂ = 20 mm
Flow-
Liquid
p= 1000 kg/m³
μ = 0.02 Pa s
Ri. A
Ro
A liquid flows through the space between a small rod and a pipe, as shown in diagram below.
The outer radius of the pipe is R₁, the inner radius of the rod is R₁, and the ratio λ
pressure difference per unit length (Ap/L) of 2000 Pa/m is applied to drive the fluid flow. The
liquid has a viscosity of μ = 0.02 Pa's.
Q = π
If the equation of volumetric flow rate (Q) of the liquid, is given as
ApR" ApR" (Ri
8μ L 8μ L
+
-20%
4
R
R₁ = AR₁ = 10 mm
+
Ro
Ri
(A) What should be the value of "n", for the equation above to be dimensionally consistent? Use
dimensional analysis.
n
(1-2²)² ApR"
8μ L
In
==.
(B) Calculate the value of volumetric flow rate in cubic meter per second when r = (Ro+
R₁)/2, and Ro = 20mm, R₁ = 10mm. Report your result with three significant figures.
Chapter 8 Solutions
Fundamentals of Aerodynamics
Ch. 8 - Consider air at a temperature of 230 K. Calculate...Ch. 8 - The temperature in the reservoir of a supersonic...Ch. 8 - At a given point in a flow, T=300K,p=1.2atm, and...Ch. 8 - At a given point in a flow, T=700R,p=1.6atm, and...Ch. 8 - Consider the isentropic flow through a supersonic...Ch. 8 - Consider the isentropic flow over an airfoil. The...Ch. 8 - The flow just upstream of a normal shock wave is...Ch. 8 - The pressure upstream of a normal shock wave is 1...Ch. 8 - The entropy increase across a normal shock wave is...Ch. 8 - The how just upstream of a normal shock wave is...
Ch. 8 - Consider a flow with a pressure and temperature of...Ch. 8 - Consider a flow with a pressure and temperature of...Ch. 8 - Repeat Problems 8.11 and 8.12 using (incorrectly)...Ch. 8 - Derive the Rayleigh Pitot tube formula, Equation...Ch. 8 - On March 16, 1990, an Air Force SR-71 set a new...Ch. 8 - In the test section of a supersonic wind tunnel, a...Ch. 8 - When the Apollo command module returned to earth...Ch. 8 - The stagnation temperature on the Apollo vehicle...Ch. 8 - Prove that the total pressure is constant...
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