How is the design of a ramjet influenced by the desired flight Mach number?
How is the design of a ramjet influenced by the desired flight Mach number?
estion 9- Ramjet Operation (15 Points): You are asked to calculate the operational parameters of an ideal ramjet engine. flame holder combustion zone Me inlet diffuser nozzle e- Nozzle exit throat-M-1 Normal shock wave Ramjet 3-Burner exit 2- Diffuser exit 00 K. Flight altitude is 10 knm Flight Mach number is 2.0. Burner exit temperature is 17 Make the following assumptions: Assume that the Mach number in the combustor is zero (stations 2 and 3) Ignore pressure losses in the...
4. The thermodynamic state of a gas in a ramjet is shown on the Ts diagram below. Assuming constant gas properties, γ = 1.4 and Cp = 1.004 kJkgK, calculate (Points 2.5) Pu=0.9 p 2 T,,-Tu= 1.650 K Pro p, = 0.12 bar To 223 Ko. bar α) 49 a. b. c. The flight Mach number, Mo The exhaust Mach number, Mo The exhaust velocity, V9, in m/s
Problem 2.3. An ideal ramjet is to fly at 20,000 ft with a Mach number of 3.5. The burner exit total temperature is to be 3200 °?? and the engine will use 145 lbm/s of air. The heating value of the fuel is 18,500 Btu/lbm. What is the diameter of the rounded exit, thrust, dimensionless thrust, and TSFC at this condition? (Assume that the temperature is 447.38°??, the static pressure is 6.747161 psia, and the specific heat ratio is 1.4...
4. A supersonic engine inlet is shown below-with a spike centerbody. Suppose the flight Mach number M1 = 2.5, and the pressure is pı = 50,000 N/m². The half-angle of the spike centerbody is 10°, as shown. For a particular mass flow through the engine, it happens that there is an oblique shock at a, and a normal shock wave standing at b. Before entering the second shock wave, the fluid expands through a Prandtl-Meyer turn, as the skech indicates....
What design features could be used to increase critical mach number of an airplane?
(a) A high speed (Mach number > 0.3) aircraft is flying at an altitude where the temperature and pressure is 2°C and 97 kPa. Its flight velocity is measured by a probe which records a dynamic pressure of 20 density is 13600 kg/ml. Find the reading of the manometer given k=1.4 and R=0.287 kJ/kg-K.
Question 2.8 Refering to the figure below, a supersonic flow with upstream Mach number, M, static pressure, pi, and static temperature, Ti, as specified in the table below, encounters a corner with a turning angle ore Determine the angle of the oblique shock, ?, the angle of the reflected wave, q, the Mach numbers M2 and M, and the downstream static pressure Ps and static temperature Ty Mi P1 M3 P3 T3 Design Data Value Unit Mach number (M) Static...
Design and implement a class called Flight that represents an airline flight. It should contain instance data that represents the airline name, flight number, and the flight’s origin and destination cities. Define the Flight constructor to accept and initialize all instance data. Include getter and setter methods for all instance data. Include a toString method that returns a one-line description of the flight. Create a driver class called FlightTest, whose main method instantiates and updates several Flight objects.
A supersonic flow of air with Mach number of M1=2.8 is deflected towards itself by 16o. What is the Mach number M2 behind the a weak oblique shock?
1. It is desired to design a linear phase, length N FIR filter via the window method. The desired amplitude response is given by the function A(u), i.e Show how to calculate the filter coefficients h(n), n 0,1,..., N-1 from A(u) if the window function is wn 1. It is desired to design a linear phase, length N FIR filter via the window method. The desired amplitude response is given by the function A(u), i.e Show how to calculate the...