According to Chegg policy, I solved question number 3 all subparts.
3. An aircraft is known to be flying at a supersonic speed. Assume the gas it...
M 3. Consider a scenario in which supersonic flow is expanded and turned by 150 through a Prandtl-Meyer expansion wave/fan. Consider the gas to be calorically perfect Air with upstream properties as follows: M1 = 4, P = 20 kPa, T = 250 K. Find: 0-150 M2 (a) freestream Prandtl-Meyer function, Vi. (b) downstream Mach number, M2. (c) downstream static pressure, P2. (d) downstream static temperature, T2.
2. Find the Mach number and air speed corresponding of 500 kPa(abs) in an air flow with a (static) pressure of 100 kPa and measured (stagnation) temperature of 500 K. DISCUSSION: Suppose that, instead of assuming that a normal shock occurs upstream of the Pitot tube, it is assumed that the flow upstream is ISENTROPIC... what would the estimated flow speed be in that case? (NOTE: A normal shock is always observed to form upstream of bluff bodies such as...
3. Air enters a constant area duct at a Mach number of 0.14, a pressure of 195 kPa, and a temperature of 25 °C. Heat is added to the air that flows through the duct at a rate of 65 kJ/kg of air. Assuming that the flow is steady and that the effects of wall friction can be ignored, find the temperature, pressure, and Mach number at which the air leaves the duct. Assume that the air behaves as a...
(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.
Consider an imaginary method to generate a supersonic flow in a two-step process of heating and cooling. Heat is first added to air at a low Mach number, increasing the Mach number until the flow is thermally choked at M = 1. Heat is then removed from the air, which further increases the Mach number (this is the imaginary part, that you were able to jump over M = 1 to the supersonic branch). Air at a pressure of 100...
Assume ideal gas, air gamma = 1.4, R = 287 J/kgK. ~ Use normal shock tables! ~ A pitot-static probe designed for subsonic flow shows the velocity calculated from the ratio of stagnation pressure to static pressure and a fixed stagnation temperature of 350 K. Determine the indicated velocity and the actual velocity when the pitot- static probe is erroneously used in supersonic flow, with a stagnation pressure to static pressure ratio of 1.5.
Can you please do this question correctly,thanks!! 183 184Question 2.6 Air is flowing at supersonic speed over a two-dimensional wedge with an upstream static pressure, P, and static temperature, T, which are defined in the table below 185 186 Value Design Data Unit 187 188 Upstream static pressure (P) 96 kPa 189 Upstream static temperature (T) 265 CK 190 Upstream mach number (M) 2.55 WATCH 191 Wedge half-angle (e) 18 UNITS 192 193 Your answers 194 a) Find the wedge...
Q1. Pressure load in re-entry capsule nose A crew capsule has re-entered Earths atmosphere and slowed to a speed of V-1134 m/s at an altitude where the static temperature is T-200 K and the static pressure is p=1 kPa. A normal shock forms upstream of the nose of the capsule. What is the pressure of the flow where it stagnates against the nose of the capsule? Assume the air behaves as a calorically perfect gas with ratio of specific heats...
temperature is standard 223k (b) Consider an airplane flying at an altitude of 10,000m. Assume atmospheric conditions from the standard atmosphere tables in the text. If the stagnation pressure measured by a pitot tube is po = 0.7929 atm, determine the Mach number of the vehicle. Also determine the air speed of the vehicle.
. A turbofan aircraft engine is flying at 720 km/h at an altitude of 6100 m, where the ambient conditions are 50 kPa and -12°C (a negative value). The pressure ratio across the compressor is 13, and the turbine inlet temperature (TIT) is 1330 K. Assuming ideal operation for all components and constant specific heats for the air at room temperature (cold air model). (a) Sketch the T-s diagram of the cycle, and determine: (b) The Mach number of the...