fall_2003_pset9

# fall_2003_pset9 - Massachusetts Institute of Technology...

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Unformatted text preview: Massachusetts Institute of Technology Department of Aeronautics and Astronautics Cambridge, MA 02139 16.01/16.02 Unified Engineering I, II Fall 2003 Problem Set 9 Name: Due Date: 11/4/03 Time Spent (min) F3 F4 F5 S12 S13 S14 M7 Study Time Announcements: Unified Engineering Fall 2003 Fluids Problems F3F5 F3. Anderson Problem 1.4 F4. A rectangular wing of chord c and span b is operating in low-speed ow. Its drag depends on the following parameters: D = f ( , , V , , b, c ) C Determine the dimensionless parameters (Pi products) which determine the drag coecient D . F5. An certain aircraft normally operates at 8km altitude, where the air properties compare to the sea level values as follows: = . 50 SL a = . 95 a SL = . 95 SL 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 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...
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## This note was uploaded on 01/28/2012 for the course AERO 16.01 taught by Professor Markdrela during the Fall '05 term at MIT.

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fall_2003_pset9 - Massachusetts Institute of Technology...

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