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Unformatted text preview: ASE 362K MidSemester Exam Tuesday, March 18th , 2008 Open Book — Answer all questions [40 points] 1) A convergent nozzle, shown below, is being run such that the Mach number in the exit is equal to
one. The air is supplied by a large tank which is at a stagnation pressure of P0. The stagnation pressure P0 is then doubled. By how much will the mass flow through the nozzle change? [Note: The
Mach number at the exit remains fixed at unity] (10 points) lexii Flame l
l l———D Mex}? = 1'00 2) A thin flat plate is at angle of attack of 8 degrees in a Mach 3 airstream. Using “shock—expansion”
theory calculate the drag coefficient of the plate. Shockexpansion theory just assumes that there are leading and trailing edge shocks and expansions as shown in the sketch below.
(10 points) 3) Air enters a ramjet combustion chamber with a velocity of 100m/s and a static temperature of 400K. Given that: a) for air, y = 1.4, R = 287 J/kgK, and CD = 1005 J/kgK, b) that air behaves as a perfect gas with a constant specific heat, c) assuming that there is no friction and d) the heating
value of the fuel is 40 MJ/kg. (i) What is the maximum amount of heat that can be added in the combustion chamber
without reducing the mass flow rate? (ii) For the qmax in part (i) above calculate the fuelair ratio. (iii) If the fuelair ratio was to be increased by 10% calculate the reduction in the mass flow
rate for the same inlet stagnation pressure and temperature. [Note: when you consider the flow through the combustion chamber you can neglect the fuel
flow rate in comparison with the air flow rate.] (20 points) 4:3 [“ 0m? 3 WC 0L5>i nw‘evJd; 30v; we. 0)‘T804 ‘3 Prm Haml mop) ﬂow.) n2) wokUL
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