Consider the isentropic flow over an airfoil. The freestream conditionscorrespond to a standard altitude of 10,000 ft and M∞ = 0.82. At a givenpoint on the airfoil, M = 1.0. Calculate p and T at this point.

Consider the isentropic flow over an airfoil. The freestream conditionscorrespond to a standard altitude of 10,000 ft and M∞ = 0.82. At a givenpoint on the airfoil, M = 1.0. Calculate p and T at this point.

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter5: Analysis Of Convection Heat Transfer

Section: Chapter Questions

Problem 5.24P: Engine oil at 100C flows over and parallel to a flat surface at a velocity of 3 m/s. Calculate the...

See similar textbooks

Related questions

Q: Flow over flat plate has velocity and temperature distribution as, u (r, x) = C, and T (r, x) = C 2…

Q: Air at 27°C and 1 atm flows over a flat plate at a speed of 2 m/s. Calculate the boundary- layer…

A: Given:T=27°Cv=2 m/sμ=1.85*10-5 Kg/ms

Q: A pipe bore diameter D and length L has fully developed laminar flow throughout the entire length…

Q: 2-Air at 30 C over a flat plate at speed of 1.2 m/sec. Calculate the boundary layer thickness at…

Q: 3-Air flows over the flat plate at velocity 3 m/s and ambint temperature 15 C.The plate is maintaned…

Q: For water flowing over a flat plate at 15°C and 3 m/s, calculate the mass flow through the boundary…

A: Given Temperature = 15o C Velocity = 3m/s Distance = 5 cm = 0.05 m To find Mass flow rate

Q: Consider the lifting flow over a circular cylinder of a given radius (R) and with a given…

Q: Calculate the total friction drag on a flat plate of length 3 m and width 1.2 m in a uniform stream…

Q: Problem 3. Air at 20°C and 1 atm (p= 1.2 kg/m³ and u= 1.8×105 kg/(m-s)) flows at 3 m/s past a sharp…

A: (a) Calculate the Reynolds's number. Re=ρvLμ=1.2311.8×10-5=2×105<5×105so flow is laminar

Q: Thrust is required to propel an airplane at a fi nite forwardvelocity. Does this imply an energy…

A: The force that allows the aeroplane to move forward is the thrust force. Thus the thrust force is…

Q: O Prove that for isentropic flow of perfect gas the effects of an area change on the flow properties…

A: Given Isentropic flow Subsonic and supersonic flow To find Relationship of isentropic flow of…

Q: Consider an airfoil in a flow with a freestream velocity of 150 ft/s. The velocity at a given point…

A: Given: The freestream velocity of the flow is V1=150 ft/s The velocity at a given point on the…

Q: A space of 25 between tWo surraces th SAF west lubricating oil at 250C (u = 0.18 Ns/m?). Plot the…

Q: Use appropriate boundary conditions to evaluate the constants in the boundary layer velocity profile…

A: Suppose a fluid moving with a velocity 'u' in a viscous flow and whose vertical distance from the…

Q: d the thickness of the boundary layer at a distance of x = 20 c

A: Re @ x =20 cm Re = ρ Vxμ = Vxν= 5 * 0.21.995 x 10-5=50125.31328 < critical reynold snumber ,…

Q: Determine the drag force exerted on the flat plate of 4 m long when air is flowing over it with a…

A: The answer is given below

Q: Consider a NACA 2412 airfoil at an angle of attack of 4 degrees. If the freestream Mach number is…

Q: Consider a large commercial airplane cruising at a speed of 1050 km/h in air at an altitude of 10 km…

A: Given, Speed of aeroplane (V)= 1050 km/h Altitude (h)= 10 km temperature (T)= −50°C = -50+273=223…

Q: The point where the fluid comes to rest is called as O a. Rest point O b. Stagnation point O c.…

A: The point where the flowing fluid comes to rest is known as stagnation point.

Q: Q4) A particle of 1 mm in diameter and density of 2500 kg/m3 is settling in a stagnant fluid in the…

Q: Consider a flat plate at zero angle of attack in an airflow at standard sea level conditions (p∞ =…

A: Given data: Sea level conditions: P∞=1.01×105 N/m2, T∞=288K, μ∞=1.7894×10-5 kg/(m.s) Also for air…

Q: Consider a diamond-wedge airfoil such as shown , with ahalf-angle ε = 10◦. The airfoil is at an…

Q: Q1: Air flows at 10 m/s past a smooth rectangular flat plate 0.3m wide and 3m long. Assuming that…

Q: 5) A wedge airfoil is placed in a supersonic flow at M 2. G. Calculate the lift and drag…

A: Given: The Mach number, M = 2.G = 2.2 The angle of attack, α = 4°

Q: Consider a rectangular wing with a NACA 23015 airfoil that has a maximum thickness of 2.7 ftand a…

A: Given:Thickness of wing,t=2.7ftLength of wing,L=20ftSo, area of…

Q: 1- Determine the velocity distribution in the velocity boundary layer assuming second degree…

A: As per our guidelines, experts can provide solution to only one problem in case of multiple…

Q: Air at 20°C and 1 atm flows at 3 m/s past a sharp flat plate2 m wide and 1 m long. (a) What is the…

A: ASSUMPTIONS: boundary layer flow with zero pressure gradient…

Q: from

Q: The velocity profile for a turbulent boundary layer over a flat plate is to be approximated by the…

A: The given velocity profile is – The two boundary conditions for boundary layer flow is – From…

Q: Consider the same Lockheed F-104 supersonic fighter shown, with the same flight conditions of Mach 2…

Q: 1. when , the flow is accelerates if the cross sectional area is increases ( a) M 1 (c) M =1 2. If…

A: Explaining , what is the value of mach number when the cross section area increases in accelerated…

Q: 1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2. Consider the isentropic flow over an airfoil. The freestream…

A: T∞ = 245 K p∞ = 4.35 × 104 N/m2 P =3.6 × 104 N/m2 Calculate the density…

Q: Consider the isentropic flow over an airfoil. The freestream conditions are T∞ = 245 K and p∞= 4.35…

A: The constant value of entropy is maintained anytime there is a reversible and adiabatic flow,…

Q: Air with uniform velocity of U is flowing over flat square-shape plates with different arrangements…

Q: SR-71 Blackbird cruised at Mach 3.2 at 80,000 ft altitude. However, it was designed to leak a finite…

A: Given data Aircraft is flying at Mach 3.2 M = 3.2Altitude = 80000 ftSpecific Heat Ratio = γ = 1.4

Q: Determine the lift coefficient of a supersonic aerofoil, approximated by a flat plate. It is flying…

A: Introduction: The lift coefficient (CL), a dimensionless coefficient, connects the lift produced by…

Q: 4.5 Determine the additive drag for an inlet and a Mach number M₁ of 0.4 at an altitude of 2000 ft.…

A: Given: The inlet area, A = 7000 in^2 = 4.516 m^2 The inlet Mach number, M1 = 0.8 The flying Mach…

Q: a smooth flat plate of length 5 m and width 2 m is moving with a velocity of 4 m/s in stationary air…

A: L= 5 m b=2 m v=4 msecρ=1.25kgm3ν=1.5×10-5 m2sec Thickness of the boundary δ in case of turbulant…

Q: Prob.7. A smooth flat plate of length 5 m and width 2 m is moving with a velocity of 4 m/s in…

A: Given data- The length of the plate is L = 5 m. The width of the plate is w = 2 m. The velocity of…

Q: Choose the most appropriate statement with respect to the pressure distribution of an airfoil. The…

A: following is the answer to the above question-

Q: An engineer is designing a subsonic wind tunnel. The test section is to have a cross-sectional area…

Q: Air is flowing past a spherical ball. Is the lift exerted on the ball zero or nonzero? Answer the…

A: When air is flowing past a spherical ball, the lift exerted on the ball is zero if the ball is…

Q: A Boeing 747 cruises at a Mach number of Ma=0.87 at an altitude of z = 13 km on a standard day. A…

A: Given that, Mach number at an altitude,Ma1=0.87,h1=13 km,The cabin is pressurized to an equivalent…

Question

Consider the isentropic flow over an airfoil. The freestream conditions
correspond to a standard altitude of 10,000 ft and M_∞ = 0.82. At a given
point on the airfoil, M = 1.0. Calculate p and T at this point.

Expert Solution

This question has been solved!

Explore an expertly crafted, step-by-step solution for a thorough understanding of key concepts.

This is a popular solution!

SEE SOLUTION Check out a sample Q&A here

Step 1

VIEW

Step 2

VIEW

Trending now

This is a popular solution!

Step by step

Solved in 2 steps

SEE SOLUTION Check out a sample Q&A here

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

Air is flowing parallel to the plate at U∞=5 m/s and T∞=300 K over the flat plate of length L=0.1 m anddepth of 1 m into the paper, at the atmospheric pressure at the same temperature as the plate. Find;a) Boundary layer thickness at the point x = L of the plateb) Find the total resistance force acting on the two surfaces of the plate.c) The velocities in the hydrodynamic boundary layer are measured by a hot wire anomemeter. Thevelocity at x=0.1 m on the x component is measured as u=3 m/s. Find the distance from the plate and they component of velocity v.
1.)A semi-cylindrical concrete structure having a radius of 5 m and length of 3 m is rested on ground. Wind (air having a density ρ=1,2 kg/m3 ) at a free-sream speed of 3 m/s with an atmospheric pressure of 100 kPa far upstream the structure blows over the structure. The air entrance to the structure is at ground level corresponding to the forward stagnation point . Since the magnitude of minimum pressure is acting on the top of the structure determine the magnitude of lift force due to the pressure difference in vertical direction .Assume flow potential ANSWER: 648 N
Air is flowing past a spherical ball. Is the lift exerted on the ball zero or nonzero? Answer the same question if the ball is spinning.
1 atm = 2116 lb/ft2 = 1.01 × 105 N/m2. Consider the isentropic flow over an airfoil. The freestream conditions areT∞ = 245 K and p∞ = 4.35 × 104 N/m2. At a point on the airfoil, thepressure is 3.6 × 104 N/m2. Calculate the density at this point.
Consider a commercial airliner flying at a speed of 540 mph (relative to the air) at analtitude of 30,000 feet. (c) With a mean molar mass of M = 28.9 g/mol, determine the Reynolds number andMach number in flight. Justify your choice of characteristic length by referencinga commercial aircraft currently in service.(d) Is this flow inviscid or viscous? Is this flow subsonic or supersonic? Qualitativelydescribe the differences between these flight regimes.
An airfoil is in a freestream where p.(assigned altitude)atm, p(density) (assigned altitude) kg/m3, and V 980 m/s. At a point on the airfoil surface, the pressure is 0.5 atm. Assuming isentropic flow, calculate the velocity at that point. assigned altitude 36.22km
Consider a rectangular wing with a NACA 23015 airfoil that has a maximum thickness of 2.7 ftand a wing span of 20ft if the freestream density, temperature and mach number are 1.22x10^-3 slugs/ft^3, 444 R and 0.2 respectively. Calculate the lift if the coefficient of lift is 0.8. English unit not metric
Consider the isentropic flow through a supersonic wind-tunnel nozzle. The reservoir properties are T0= 500 K and p0 = 10 atm. If p (corresponds to your assigned altitude) at the nozzle exit, calculate the exit temperature and density.ASSIGNED ALTITUDE = 9522 ft
A) What is an adverse pressure gradient, and where does it occur on an airfoil (Show that onan airfoil using a free hand sketch)?B) What causes the flow to separate from an airfoil?C) What are the two major consequences of flow separation?D) A B-2A aircraft is flying at H ft in standard day conditions at a velocity V kn. If the meanchord length is C ft.i- Find the overall or total Reynolds number for the aircraft.ii- Find the percentage of the wing chord where laminar flow is present, if Reynoldsnumber is 500,000.
Consider laminar flow past a sharp flat plate of width b andlength L. What percentage of the friction drag on the plateis carried by the rear half of the plate?
Consider the isentropic flow over an airfoil. The freestream conditions areT∞ = 245 K and p∞= 4.35 × 10^4 N/m^2 . At a point on the airfoil, the pressure is 3.6 × 10^4N/m^2 . Calculate the density at this point using Energy equation.
Thrust is required to propel an airplane at a fi nite forwardvelocity. Does this imply an energy loss to the system?Explain the concepts of thrust and drag in terms of the fi rstlaw of thermodynamics.