please draw in autocad and share .dwg file as well
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Determine the shear and moment as a function of x, and then draw the shear and moment diagrams.
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A turboprop engine consists of a diffuser,compressor, combustor, turbine, and nozzle. Theturbine drives a propeller as well as thecompressor. Air enters the diffuser with avolumetric flow rate of 83.7 m3/s at 40 kPa, 240 K,and a velocity of 180 m/s, and deceleratesessentially to zero velocity. The compressorpressure ratio is 10 and the compressor has anisentropic efficiency of 85%. The turbine inlettemperature is 1140 K, and its isentropic efficiencyis 85%. The turbine exit pressure is 50 kPa. Flowthrough the diffuser and nozzle is isentropic. Usingan air-standard analysis, determine: (a) the powerdelivered to the propeller, in MW. (b) the velocity atthe nozzle exit, in m/s. Neglect kinetic energyexcept at the diffuser inlet and the nozzle exit
Draw a SMD for the transverse axis of the S-IC using symbolic values (no numbers). The diagram should reflect: 1. A constant, even transverse pressure the vehicle experiences due to wind at the pad (note that this must include the wind pressure experienced by the upper stages, collectively referred to as šš). 2. The fixed base of the vehicle on the pad. 3. A fueling arm located at š/2 from the base of the rocket that exerts a load šš in a direction counter to the wind. šš is not large enough to counteract all the shear experienced by the stage at station š/2. 07 Hint: for this problem, continue drawing the SMD along the X axis, with the fixed base at the bottom of the rocket.