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1 what is the speed of a sound wave in air at 300degk what is the speed in helium at the same temperature can you
a blowdown wind tunnel exits to atmospheric pressure in the working section where the cross-sectional area is 004 m2
a large reservoir maintains air at 68times105 p a and 15degc the air flows isentropically through a convergent and
1 an air flow with a mach number of 20 passes through an oblique shock wave inclined at an angle of 45deg find the
1 an air flow with an initial mach number of 15 and initial pressure p1 is expanded isentropically by passing through a
1 air at 20degc and atmospheric pressure flows horizontally through a collection chamber 3 m high and 5 m long the air
water flows smoothly over a small bump in a channel of constant width as shown in figure p1011 at any cross-section the
1 the water depth upstream of a stationary hydraulic jump is 1 m while the depth after the jump is 2 m find the
a circular jet of water impinges on a flat plate as shown in figure p1049 the water spreads out equally in all
1 a surge of depth h moves into a stagnant tidal pool of depth 1 m at a speed of 6 ms relative to a stationary observer
a tidal bore is moving upstream into a river of depth 1 m and constant width and the bore raises the water level by 1 m
1 a surge is moving at 9 f ts into a basin of depth 14 f t where the speed is zero find the water depth behind the
1 a surge is moving at 10 f ts into a depth 2 f t where the speed is zero find the water depth behind the surge2 a
air with a stagnation temperature of 700degk is compressed by a normal shock if the upstream mach number is 30 find the
1 find the maximum increase in density across a shock wave for a gas with gamma 142 a blowdown wind tunnel is supplied
1 a pelton wheel of 4 m diameter operates with a head of 1000 m estimate the flow rate and power output of the machine
a turbine of the francis type operates with a head of 200 m and flow rate of 3m3s the peak efficiency occurs at a head
air having an initial mach number of 24 a freestream static pressure of 105 p a and a static temperature of 270degk is
a supersonic flow passes over a symmetrical wedge of semi-angle alpha 10deg at the leading edge an attached shock of
a rocket motor is designed to give 10 000 n thrust at 10 000 m altitude the combustion chamber pressure and temperature
air at 0degc and atmospheric pressure flows horizontally at a speed of 05 ms through a collection chamber 4 m high and