![EBK FUNDAMENTALS OF AERODYNAMICS](https://www.bartleby.com/isbn_cover_images/9781259681486/9781259681486_largeCoverImage.jpg)
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
![Check Mark](/static/check-mark.png)
Want to see the full answer?
Check out a sample textbook solution![Blurred answer](/static/blurred-answer.jpg)
Chapter 11 Solutions
EBK FUNDAMENTALS OF AERODYNAMICS
- Wind 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_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_forwardOn 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_forward
- 2. 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_forwardQI) 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_forward
- Q2-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_forwardWith 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_forward
- What 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_forwardExample 2. A high-speed AC 130 gunship is flying at a pressure altitude of 10 km. A Pitot tube on the wingtip measures a pressure of 4.24 x 10ª N/m2. Calculate the Mach number at which the aircraft is flying. Solution: Solving for P1 at an altitude of 10000 m, we get 2.65 x 104 N/m2 k-1 1.4-1 Po k 4.24 x 104) 1.4 M? k – 1 - 1 - 1 1.4 – 1 2.65 x 104 M? = 0.719 M1 = 0.848arrow_forward
- Elements Of ElectromagneticsMechanical EngineeringISBN:9780190698614Author:Sadiku, Matthew N. O.Publisher:Oxford University PressMechanics of Materials (10th Edition)Mechanical EngineeringISBN:9780134319650Author:Russell C. HibbelerPublisher:PEARSONThermodynamics: An Engineering ApproachMechanical EngineeringISBN:9781259822674Author:Yunus A. Cengel Dr., Michael A. BolesPublisher:McGraw-Hill Education
- Control Systems EngineeringMechanical EngineeringISBN:9781118170519Author:Norman S. NisePublisher:WILEYMechanics of Materials (MindTap Course List)Mechanical EngineeringISBN:9781337093347Author:Barry J. Goodno, James M. GerePublisher:Cengage LearningEngineering Mechanics: StaticsMechanical EngineeringISBN:9781118807330Author:James L. Meriam, L. G. Kraige, J. N. BoltonPublisher:WILEY
![Text book image](https://www.bartleby.com/isbn_cover_images/9780190698614/9780190698614_smallCoverImage.gif)
![Text book image](https://www.bartleby.com/isbn_cover_images/9780134319650/9780134319650_smallCoverImage.gif)
![Text book image](https://www.bartleby.com/isbn_cover_images/9781259822674/9781259822674_smallCoverImage.gif)
![Text book image](https://www.bartleby.com/isbn_cover_images/9781118170519/9781118170519_smallCoverImage.gif)
![Text book image](https://www.bartleby.com/isbn_cover_images/9781337093347/9781337093347_smallCoverImage.gif)
![Text book image](https://www.bartleby.com/isbn_cover_images/9781118807330/9781118807330_smallCoverImage.gif)