k= 1.4 and R=287. please help 1. (20) In a converging nozzle, at the throat the...
k= 1.4 and R=287. please help 1. (20) In a converging nozzle, at the throat the area is A,- 0.01 m2 and velocity is V 300 m/s. The mass flow rate is rn 6 kg/s. The density in the reservoir is po 2.75 kg/m2 Is the flow choked? Prove it! Find the temperature in the reservoir, To, and at the throat T, both in °C.
A converging-diverging nozzle has a throat area of 1 cm2 and an exit area of 4 cm2. The inlet stagnation conditions are Po 500 kPa and To 300 K. The nozzle discharges to an infinite surroundings at Po. The flowing medium is air as a perfect gas with k-1.4 Answer the following: i What are the two isentropic flow solutions for this nozzle with M 1 at the throat? What are the Mach number, P, Po and T, To at...
Question 1.4 A convergent-divergent nozzle is designed to operate with isentropic flow with an exit Mach number, Me. The flowin the nozzle is supplied from a reservoir of air with a static pressure ofPr and a static temperature of Tr and the nozzle has a throat area, AT, as specified in the table below Value Unit Design Data Exit Mach number (ME) 0.55 Area of throat (AT) 600 kPa Reservoir static pressure (PR) 380 WAT Reservoir static temperature (TR) kPa...
Can you please help me with part (e), thanks! A B 72 Question 1.4 A convergent-divergent nozzle is designed to operate with isentropic flow with an exit Mach number, Me. The flow in the nozzle is supplied from a reservoir of air with a static pressure of PR and a static temperature of TR and the nozzle has a throat area, AT, as specified in the table below 73 Design Data Value Unit 75 Exit Mach number (ME) 76 77...
Poblem Comergini sentropie regim (no shock waves) Consider isentropic flow through a converging-diverging nozzle. The exit area of the nozzle is , and the throat area of the nozzle is . The air entering the nozzle has stagnation conditions: , and Use Figure D.1 or Table D (a) Calculate the mass flow rate for choked flow (that is, sonic flow at the throat). Hints: See Section 11.7, use Figure D.1 to find density and temperature at M 1 (throat), find...
A nozzle is designed to deliver a supersonic air flow, R = 287 J/Kg/K, of Mach M = 2.19 The reservoir has a pressure of p0 = 648kPa and T0= 300K. The nozzle exit has an area of 0.233 m^2. The nozzle flow exits into an environment that is kept at constant pressure pb which matches the exit pressure of the nozzle. As long as there are no shock waves appearing in – or outside the nozzle, the complete flow...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
Consider a converging-diverging nozzle with an exit-to-throat area ratio (Ae/At) of 5. The reservoir pressure (po) and temperature (To) are equal to 5 atm and 600K, respectively. Determine exit Mach number, temperature and pressure values for normal shock at 3/4 of the diverging portion.
Air, at po = 160 lbf/in2 and To = 300°F, flows isentropically through a converging-diverging nozzle. At section 1, where A1 = 288 in2, the velocity is V1 = 2068 ft/s. Calculate the inlet Mach number (Ma1) and the throat area (A*). The inlet Mach number is-------- . The throat area is---------- ft2.es Determine the inlet pressure (p1) and the mass flow rate (m.). Round the final answer to three decimal places. The inlet pressure is ----------- lbf/ft2. The mass...