Engineering, 14.04.2020 21:43 boonkgang6821
Assuming a lift curve slope of 0.11 per degree angle of attack for a two-dimensional airfoil, calculate the lift coefficients at 2, 6 and 10 degrees angle of attack for:
a. A symmetric airfoil.
b. A positively cambered airfoil with a zero lift angle of attack of -1.3 degrees.
c. A reflexed airfoil with a zero lift angle of attack of 1.75 degrees.
Answers: 1
Engineering, 03.07.2019 15:10, breannaasmith1122
Two flowing streams of argon gas are adiabatically mixed to form a single flow/stream. one stream is 1.5 kg/s at 400 kpa and 200 c while the second stream is 2kg/s at 500 kpa and 100 ? . it is stated that the exit state of the mixed single flow of argon gas is 150 c and 300 kpa. assuming there is no work output or input during the mixing process, does this process violate either the first or the second law or both? explain and state all your assumptions.
Answers: 1
Engineering, 04.07.2019 18:10, lerasteidl
Determine whether or not it is possible to compress air adiabatically from k to 140 kpa and 400 k. what is the entropy change during this process?
Answers: 3
Engineering, 04.07.2019 18:10, genyjoannerubiera
Assuming compressible flow of air and that the measurements are done at flagstaff a pitot static tube that gives the difference of total and static pressure measures 0.35 m of mercury. what is the velocity of air? assume the temperature to be 300k. (submit your excel or matlab calculation sheet)
Answers: 1
Engineering, 04.07.2019 18:20, hayleymckee
Steam enters a converging nozzle at 3.0 mpa and 500°c with a at 1.8 mpa. for a nozzle exit area of 32 cm2, determine the exit velocity, mass flow rate, and exit mach number if the nozzle: negligible velocity, and it exits (a) is isentropic (b) has an efficiency of 94 percent
Answers: 2
Assuming a lift curve slope of 0.11 per degree angle of attack for a two-dimensional airfoil, calcul...
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