1. A substance flows through a horizontal pipe at the rate of "Z" ft3 per min. Derive
a working equation to determine the difference in pressure between two points
with diameter "X" and "Y" ft. Assume the pipe is converging.
Prepare for your exams
Study with the several resources on Docsity
Earn points to download
Earn points by helping other students or get them with a premium plan
Guidelines and tips
Prepare for your exams
Study with the several resources on Docsity
Earn points to download
Earn points by helping other students or get them with a premium plan
Aerodynamics Sample Problems, Exams of Aerodynamics
5 sample problems that is all about the earth's atmosphere, basic standard atmosphere
Typology: Exams
2022/2023
1 / 5
This page cannot be seen from the preview
Don't miss anything!
Related documents
Partial preview of the text
Download Aerodynamics Sample Problems and more Exams Aerodynamics in PDF only on Docsity!
- A substance flows through a horizontal pipe at the rate of "Z" ft^3 per min. Derive a working equation to determine the difference in pressure between two points with diameter "X" and "Y" ft. Assume the pipe is converging.
- Air is flowing horizontally at a speed of "J" mph through a duct with "L" ft^2 in cross section. If a U-tube manometer shows a difference in pressure between the through and main section of "dp" psf, derive a working equation for the cross- section area "U" of the throat? Assume incompressible and has a density at standard condition.
- A circular pipe, 100 ft. long gradually tapers from 3 ft in diameter at one end to 2 ft. in diameter at the other end. Fluid flowing from the bigger toward to smaller end. What is the rate of change in velocity per run if the velocity there is 80 fps.
- Consider a rocket burning hydrogen and oxygen; the combustion chamber pressure and temperature are 25 atm and 3517 K, respectively. The area of the rocket nozzle throat is 0.1 m^2 with a system flow rate is at 122 kgps. The area of the exit is designed so that exit pressure exactly equals to the ambient pressure at a standard altitude of 30 km. For the gas mixture, assume k=1.22 and R = 519. Nm / (kg)(K). Calculate (a) Area of the exit section (b) Mach number at the exit section.