Fundamentals of Aerodynamics
6th Edition
ISBN: 9781259129919
Author: John D. Anderson Jr.
Publisher: McGraw-Hill Education
expand_more
expand_more
format_list_bulleted
Videos
Textbook Question
Chapter 11, Problem 11.6P
Consider an airfoil in a Mach 0.5 freestream. At a given point on the airfoil, the local Mach number is 0.86. Using the compressible flow tables at the back of this book, calculate the pressure coefficient at that point. Check your answer using the appropriate analytical equation from this chapter. [Note: This problem is analogous to an incompressible problem where the freestream velocity and the velocity at a point are given, and the pressure coefficient is calculated from Equation
Expert Solution & Answer
Want to see the full answer?
Check out a sample textbook solution
Students have asked these similar questions
Consider an airfoil in a Mach 0.5 freestream. At a given point on theairfoil, the local Mach number is 0.86. calculate the pressure coefficient at that point. [Note: In an incompressible flow, the pressure coefficient at any point in the flow is a unique function of the local velocity at that point and the freestream velocity. In the present problem, we see that Mach number is the relevant property for a compressible flow—not velocity. The pressure coefficient for an inviscid compressible flow is a unique function of the local Mach number and the freestream Mach number.]
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. Briefly describe Pascal's Law. Provide an examples of Pascal's Law applications in
engineering.
2. What is Reynolds Number? what is the purpose of Reynolds number? State the
equation of Reynolds number. Also briefly explain what is Mach number and state its
equation.
Rriefly oKnlain Rornoulli's pringinl
State the Rorno.lli's oguation gnd dofina ongh
Chapter 11 Solutions
Fundamentals of Aerodynamics
Ch. 11 - Consider a subsonic compressible flow in cartesian...Ch. 11 - Using the Prandtl-Glauert rule, calculate the lift...Ch. 11 - Under low-speed incompressible flow conditions,...Ch. 11 - In low-speed incompressible flow, the peak...Ch. 11 - For a given airfoil, the critical Mach number is...Ch. 11 - Consider an airfoil in a Mach 0.5 freestream. At a...Ch. 11 - Prob. 11.7PCh. 11 - Consider the flow over a circular cylinder; the...Ch. 11 - In Problem 11.8, the critical Mach number for a...
Knowledge Booster
Learn more about
Need a deep-dive on the concept behind this application? Look no further. Learn more about this topic, mechanical-engineering and related others by exploring similar questions and additional content below.Similar questions
- write MATLAB scripts to solve the following. Give MATLAB CODE : Que: Air flowing at Mach 2.5 with a pressure of 60 kPa and a temperature of 2020°C passes over a wedge which turns the flow through an angle of 44 leading to the generation of oblique shock waves One of the oblique shock waves impinges on a flat wall, which is parallel to the flow upstream of the wedge and is. " from it Find the pressure and velocity behind the reflected shock wave GIVE MATLAB CODE TO SOLVE ?arrow_forwardWhich of the following statement is NOT correct about the Mach number? If the Mach number value is between 0.8 and 1.2, then the flow is supersonic. The internal duct flow analysis mainly depends only two types of flow, supersonic and subsonic flow. If the Mach number value is between 0.3 and 0.8, then the flow is subsonic. Density effects are negligible for Mach number less than 0.3.arrow_forwardWind provides an increasingly important source of renewable energy in certain locations of the world. In fact, wind was the second largest renewable energy source worldwide (after hydropower!) and provided more than six percent of global electricity in 2020; in the U.S. that number was 8.4%. Suppose that wind turbines can convert up to 30% of the kinetic energy of incoming wind blowing through their blades into electricity (i.e., useful shaft work). In the following, we will analyze the power output of a wind turbine with a diameter of d 80 m placed at an offshore location where the wind blows steadily at an average speed of 20 knots. Explicitly state all relevant approximations or assumptions. = (a) Draw a diagram that includes appropriate elements for assessing the amount of work extracted from the wind turbine. Your diagram should have annotated any known or approximated proper- ties. What is your system and surroundings? What kind of boundary divides these two? Hint: In terms of…arrow_forward
- On October 3, 1967, pilot William J. "Pete" Knight set a world record that still stands to this day for the fastest flight by a crewed, powered aircraft by flying the North American Aviation X-15 as fast as Mach 6.7 at an altitude of 102,000 ft above sea level. Mach number is the ratio of an object’s velocity to the local speed of sound. Using the table for atmospheric properties with respect to altitude, calculate the speed of sound at an altitude of 100,000 ft. What must have been the velocity of the X-15?arrow_forward2. A particle is moving in air at sea level where the temperature is 18°C. The two disturbance spheres created by the particle at points A and B are shown in the figure below. Determine the Mach no. and velocity of the particle. (Hint: For different time intervals choose the first sphere i.e. the bigger) Ans: 0.5, 171 m-s?. 9m 3m Particle <arrow_forwardQuestion 13 A projectile travels at a speed of 260 m/s in air where the temperature is -10 °C. Find the Mach number. (Take R = 287 J/kg K and y = 1.4.) O 0.22 O 0.8 O 4.1 O 1.25 A Moving to another question will save this response.arrow_forward
- QI) An observer hears a supersonic projectile that produces Mach waves after the projectile traveled 900 m past him. If the projectile flies at 950 m/s, estimate the altitude of the projectile.arrow_forwardQ2-A model of supersonic jet fighter is to be tested in wind tunnel for dynamic similarity. any equations a- If the flow is considered to be isentropic, what dimensionless parameters must be the same for both prototype and model? b- Can we measure the Mach number of the jet experimentally ?How? Q3- Calculate the velocity of the sound at (27 C) in the following medias:- a- Air b- Water c- Steelarrow_forwardAn aircraft cruising at 1000-m elevation, z, above you moves past in a flyby. It is moving with a Mach number equal to 1.5 and the ambient temperature is 20 °C. How many seconds after the plane passes overhead do you expect to wait before you hear the aircraft? k = 1.4, R = 287 J/kg.K Mach cone Aircraft moving with velocity V and Mach number Maarrow_forward
- With the aid of diagrams, explain what are Mach waves and how they are formed. From your understanding, how can the speed of a fighter aircraft model inside the wind tunnel can be estimatedby observing the Mach wave angle using optical measurements?arrow_forwardWhat is the rule of thumb about the Mach number limit in order that the incompressible flow approximation is reasonable? Explain why wind tunnel results would be incorrect if this rule of thumb were violated.arrow_forwardThe altimeter of a high speed business aircraft reads 3900 ft. A pitot tube situated on the fuselage reads 2620 psf. Calculate the aircraft's Mach number. Identify if Mach number is supersonic or subsonic? Round off answer to 2 decimal places.arrow_forward
arrow_back_ios
SEE MORE QUESTIONS
arrow_forward_ios
Recommended textbooks for you
Elements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University Press
Mechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSON
Thermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEY
Mechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage Learning
Engineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEY
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
Intro to Compressible Flows — Lesson 1; Author: Ansys Learning;https://www.youtube.com/watch?v=OgR6j8TzA5Y;License: Standard Youtube License