Engineering, 26.02.2020 01:45 Miguel1310
At the inlet to the ombustor of a supersonic ramjet(SCRAMjet), the flow Mach number is supersonic. For the fuel-air ratio(by mass) of 0.03 and a combustor exit temperature of 4800 degree R, calculate the inlet Mach number above which the flow will be unchoked. Assume one dimensional frictionless flow with lamda = 1.4, with the heat release per slug of fuel equal to 4.5x10^8 ft-lb. Also calculate change in entropy for the process
Answers: 1
Another question on Engineering
Engineering, 04.07.2019 18:10
Burgers vector is generally parallel to the dislocation line. a)-true b)-false
Answers: 2
Engineering, 04.07.2019 18:20
Air flows over a heated plate à t a velocity of 50m/s. the local skin factor coefficient at a point on a plate is 0.004. estimate the local heat transfer coefficient at this point.the following property data for air are given: density = 0.88kg/m3 , viscosity 2.286 x 10 ^-5 kgm/s , k = 0.035w/mk ,cp = 1.001kj/kgk. use colburn reynolds analogy.
Answers: 1
Engineering, 04.07.2019 19:10
The sum of the normal stresses does not change as the stress state rotates through an angle. a)-trune b)- false
Answers: 2
Engineering, 04.07.2019 19:10
In general, how do thermosetting plastics compare to thermoplastics in mechanical and physical properties?
Answers: 3
You know the right answer?
At the inlet to the ombustor of a supersonic ramjet(SCRAMjet), the flow Mach number is supersonic. F...
Questions
Computers and Technology, 05.11.2020 23:20
Mathematics, 05.11.2020 23:20
History, 05.11.2020 23:20
English, 05.11.2020 23:20
Mathematics, 05.11.2020 23:20
Mathematics, 05.11.2020 23:20
History, 05.11.2020 23:20
Mathematics, 05.11.2020 23:20
