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A piston cylinder system containing 0.5 kg of air is compressed from a volume of 0.35 m3 to a volume of 0.1 m3. If the initial pressure was 150 kPa and the process can be modeled as a polytropic process with n = 1.4 , determine the change in temperature, the change in internal energy, the work, and heat transfer. Assume air behaves as an ideal gas with constant specific heats of cp = 1.029 kJ/kg-K and cv= 0.742 kJ/kg-K.
steam enters the first turbine stage of a vapor power cycle with reheat and regeneration at 32 mpa 600degc and expands
this would provide you with a set of Reynolds numbers. Next, using the integral method, determine the velocity profiles within the boundary layer to be followed by determination of the heat transfer coefficient values for your selected Reynolds numbe..
suppose we wish to test the hypotheses ho u15 h1 u does not 15 where we know that sigma2 9.0. if the true mean is
the lifetime in hours y of an electronic component is a random variable with density function given bynbspfy1100 e-y100
air flows steadily through a constant-area duct. at section 1 the air is at 400 kpa abs 325k and 150 ms. as a result of
For the preliminary design a power of 0.5kW/m^3 volume is to be used. Calculate the dimensions of the agitation system, rpm, and kW power.
a crate containing 40 bricks each of mass 1.3kg is placed on a storage framework as shown.a calculate the reaction
the wheel in fig. 10-27 has eight equally spaced spokes and a radius of 30 cm. it is mounted on a fixed axle and is
the acceleration of a particle is defined by the relation akt2. a knowing that v-8fts when t0 and that v 8fts when t2s
Show that the total true strain is the sum of the true strains in each step, that is the true strains are additive. Show that using engineering strains, the strain for each step cannot be added to obtain the total strain.
a construction crew lifts about 560 lb of material serveral times during the day from a flatbed truck to a 32 foot
A high performance F-16 fighter is flying at Mach 0.96 at sea level. What is the air temperature at the stagnation point at the leading edge of the wing?
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