Now suppose that your supersonic vehicle is cruising at a velocity of 2178 m/s and the estimated engine specific impulse is 1050 sec. It cruises at a constant lift-to-drag ratio of 2.5. The vehicle takeoff weight is 70 kN, and 40% of this weight is the fuel. Compute the range in km. Will you make it from LA to Tokyo with this amount offuel ? Please show all work!!

derive an expression for the mass flowrate of air for a C-D nozzle arrangement operating in choked flow conditions. Hint: start with the fact that: mmax = p* A*V * show all your steps. upload your answer here.

I need an answer quickly please ?

3. The NASA X-43 flies at a Mach number of 9.4 at an altitude of 30,000 m, where thepressure is 1171.8 Pa and the temperature is 226 K. If a supersonic wind tunnel isdesigned to reproduce these conditions, calculate the following:(a) The velocity (m/s), total/stagnation temperature (K), and total/stagnation pres-sure (kPa) in the test section.(b) The velocity (m/s), total temperature (K), and total pressure (kPa) behind thenormal shock formed in front of a blunt surface in the test section.(c) The change in entropy across this normal shock.

1. Consider a low-speed subsonic wind tunnel designed with a reservoir cross-sectional area A, = 2 m2 and a test-section cross-sectional area A2 = 0.5 m2. The pressure in the test section is P2 = 1 atm. Assume constant density equal to standard sea level density, calculate the pressure (in kPa) required in the reservoir, P1, necessary to achieve a flow velocity V2: 40 m/s in the test section. a. From item no. 1, calculate the mass flow rate (in kg/s) through the wind tunnel. b. Calculate the Mach number of the vehicle in air. c. Calculate the Mach number of the vehicle in hydrogen.

Please solve this question step by step and in clear writing. There is a sub question related to the main question. PLEASE ANSWER THAT AS WELL. Thanks!

Assume that, at a point on the wing of the concorde supersonic transport, the air temperature is -19.3c and the pressure is 1.75x10^4 N/m 2. Calculate the density (in kg/m^3) at this point. Note: Specific Heat of Air in Metric Unit, R = 287j/kg*K

Please show all work of a,b,&c. A supersonic converging-diverging nozzle is near the exit of a turbojet engine. Its cross-section is circular. The gas has the properties of air, and the flow is isentropic. At the throat location (the minimum area) the air flow is choked (is Mach one) and the throat has diameter of 20 cm.

5.7 When the reservoir pressure and temperature of a supersonic wind tunnel are 15 atm and 750 K, respectively, the mass flow is 1.5 kg/s. If the reservoir conditions are changed to p, 20 atm and T, = 600 K, calculate the mass flow.

Long flights at midlatitudes in the Northern Hemisphere encounter the jet stream, an eastward airflow that can affect a plane's speed relative to Earth's surface. If a pilot maintains a certain speed relative to the air (the plane's airspeed), the speed relative to the surface (the plane's ground speed) is more when the flight is in the direction of the jet stream and less when the flight is opposite the jet stream. Suppose a round-trip flight is scheduled between two cities separated by 3200 km, with the outgoing flight in the direction of the jet stream and the return flight opposite it. The airline computer advises an airspeed of 810 km/h, for which the difference in flight times for the outgoing and return flights is 72 min. What jet-stream speed is the computer using?