Problem 4. High-speed aircraft use "air data computers" to compute air speed from Pitot-static tubemeasurements of the stagnation pressure and static pressure. (a) Plot the percent error in computing the Machnumber assuming incompressibility (thus, using the Bernoulli equation) versus actual Mach number forMa = 0.1 to Ma=0.9. (b) For an aircraft cruising at an altitude of z = 12 km, plot the speed calculatedassuming incompressible flow and accounting for compressibility versus actual Mach number for Ma = 0.1 toMa = 0.9.

Given Data and Assumptions,Specific heat ratio for air, γ = 1.4Gas constant for air, R = 287 J/(kg…

Answered: Problem 4. High-speed aircraft use "air…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

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.
1.AB
The mass flow rate of a calorically perfect gas (C₁ = constant) through a Convergent-Divergent nozzle is given by, m = A Pt VT₁ M (1+ y +1 YM²) 2(3-1) (a) Derive the above relation from fundamental principals. Here, P₁, is total (or Stagnation) pressure and T₁ is total temperature, M is Mach number, A is local area of nozzle. (b) Prove mathematically that the maximum airflow limit occurs when the Mach number is equal to one and obtain below relation. m A Pt √√Tt Note: The limiting of the maximum mass flow rate when M =1, is called choking of the flow or Choked flow. Hint: https://www.grc.nasa.gov/www/k-12/rocket/mflchk.html y+1 2(y-1) √(4¹) R
Consider steady, isentropic flow of air through a duct with varying area. At section 1, p1 = 15 kPa (abs), T = 10°C, Vị = 592 m/s, A1 = 0.25 m². At a downstream section 2, T2 = 137°C, Maz = 0.75. Determine: a. Mach number, Mai b. sketch geometry of the duct c. mass flow rate [kg/s] d. pressure, P2 [kPa] e. cross-sectional area, A2 [m2]
A flow with Mach number M1 = 2 and pressure p1 = 1 atm is turned away from itself twice,first through an angle of 10 deg and then through a second angle of 20 deg. Compute the Machnumber and the static pressure downstream of the second turn. Then, suppose that the original flow(M1 = 2 and p1 = 1 atm) is turned away from itself through a single turn of 30 deg. Compute theMach number and static pressure downstream of this turn, and show that the values are the sameas for the first flow with two turns totaling 30 deg.3
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.
For Air: y = 1.4 PART B Question B1 a) With the aid of sketches give a clear account of the operation of convergent nozzles as a function of back pressure. In your answer clearly indicate the critical points (pressure ratios) along the pressure ratio axis. b) Determine the required area ratio A part of the expansion of new teaching and research facilities at QMUL, a new two dimensional blow- down supersonic jet facility is going to be designed, manufactured and installed at our Whitehead Aeronautical Laboratory, Figure QB1. The design Mach number for this facility is M₁ = 2.0. A = A₁ A R=287J/kg K A₁ location at which the area ratio ( A₁ c) What should be the supply pressure to the nozzle (P) in order to have a normal shock wave at a Ax =) is 1.5? A Settling Chamber Po To for this design Mach number. d) For part c, what would be the discharge mass flow rate per unit throat area? You may assume P =105 N/m² and To = 300K. atm Convergent-Divergent Nozzle A AX Schematic of a Supersonic Jet…
At a section in a nozzle (air flow), following properties are known. Po = 1000 KPa; To=500k ; V = 200 m/see é) The temperature (T) at this section is (in K), a. 480; b. 500; c. 520; d. 540; e.560 (ti) The Mach number (M) i's, a. 0.26 ; b. 0:36 ; C. 0.46;d.0.56;e.a66 3.
5.3 The reservoir pressure of a supersonic wind tunnel is 5 atm. A static pressure probe is moved along the centerline of the nozzle, taking measurements at various stations. For these probe measurements, calculate the local Mach number and area ratio: a. 4.00 atm b. 2.64 atm c. 0.50 atm
Q2.B
a) A convergent nozzle with a given area ratio is supplied with air at a constant stagnation pressure Poand a constant stagnation temperature To. With the aid of a sketch plot the nozzle mass flow rate as a function of pressure ratio () across P the nozzle. In your answer indicate the critical value of the pressure ratio. For air you may assume y = 1.4 and R = 287J/kg K. b) The engine of a supersonic aircraft is equipped with a convergent-divergent nozzle. A A, A -4.0).Determine the design subsonic and supersonic Mach numbers for this area ratio. You may assume the combustion products have the same properties as air and the expansion process through the nozzle is isentropic. The nozzle's area ratio is ( c) Determine at what pressure ratios ( ) a normal shock wave appears in the P divergent part of the nozzle at a location where -3.0) Aheck A₁
Q2: Air (y = 1.4) enters a converging-diverging diffuser with a Mach number of 2.8, static pressure pi of 100 kPa, and a static temperature of 20°C. For the flow situation shown in Figure, find the exit velocity, exit static pressure, and exit stagnation pressure. Ans: Ve = 55.093 m/s; Pe = 2236.678 kPa; Poe = 2252.44 kPa i M₁ = 2.8 A₁ = 0.10 m² A₂ = 0.50 m² A₁ = 0.25 m²

SEE MORE QUESTIONS

Recommended textbooks for you

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Elements Of Electromagnetics

Mechanical Engineering

ISBN:

9780190698614

Author:

Sadiku, Matthew N. O.

Publisher:

Oxford University Press

Mechanics of Materials (10th Edition)

Mechanical Engineering

ISBN:

9780134319650

Author:

Russell C. Hibbeler

Publisher:

PEARSON

Thermodynamics: An Engineering Approach

Mechanical Engineering

ISBN:

9781259822674

Author:

Yunus A. Cengel Dr., Michael A. Boles

Publisher:

McGraw-Hill Education

Control Systems Engineering

Mechanical Engineering

ISBN:

9781118170519

Author:

Norman S. Nise

Publisher:

WILEY

Mechanics of Materials (MindTap Course List)

Mechanical Engineering

ISBN:

9781337093347

Author:

Barry J. Goodno, James M. Gere

Publisher:

Cengage Learning

Engineering Mechanics: Statics

Mechanical Engineering

ISBN:

9781118807330

Author:

James L. Meriam, L. G. Kraige, J. N. Bolton

Publisher:

WILEY

SEE MORE TEXTBOOKS