
Study with the several resources on Docsity
Earn points by helping other students or get them with a premium plan
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
Community
Ask the community for help and clear up your study doubts
Discover the best universities in your country according to Docsity users
Free resources
Download our free guides on studying techniques, anxiety management strategies, and thesis advice from Docsity tutors
Prof. Makarand Bhatnagar assigned this task at Banaras Hindu University for Aeronatical Engineering and Fluid Mechanics. It includes: Air, Fluid, Craft, Tunnel, Wind, Wright, Altitude, Vescocity, Operation, Pressure, Density
Typology: Exercises
1 / 1
This page cannot be seen from the preview
Don't miss anything!
Unified Engineering Fall 2003
F5. An certain aircraft normally operates at 8km altitude, where the air properties compare to the sea level values as follows: � = 0. 50 �SL a = 0. 95 aSL μ = 0. 95 μSL a) A 1/4 scale model of an aircraft is to be tested in an wind tunnel at sea level conditions. Is it possible to match both the Reynolds number and Mach number to those of the actual aircraft at altitude? Explain why or why not. b) The Wright Brothers Wind Tunnel was designed to be pressurized during operation, as a means of increasing the air density �. The air temperature in the tunnel is still maintained at a normal 300 K, so that the speed of sound a and air viscosity μ inside the tunnel are unaffected by the pressurization, and are equal to their normal sea level values. Determine the pressure (in atmospheres) at which the tunnel must be operated to match the flight Reynolds and Mach numbers.