Fluid Mechanics 8th Edition

ISBN 13

978-0073398273

ISBN 10

0073398276

Authors

Frank White

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66 documents found.

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Aeronautical Engineering Chapter 1 Homework Sometimes We Can Develop Equations And Solve Practical

Problem 1.C1 Sometimes we can develop equations and solve practical problems by knowing nothing more than the dimensions of the key parameters in the problem. For example, consider the heat loss through a window in a building. Window efficiency is rated in terms of R value, which has

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 1 Homework The British Chemist Sir Cyril Hinshelwood Quipped That Fluid

Solution 1.80 First convert 1180 ft/s to 360 m/s. With T2 given as 223 K, evaluate the speed of sound at section 2, assuming, as stated, an ideal gas: This kind of calculation will be a large part of the material in Chap. 9, Compressible Flow. 22222221.4(287

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 1 Homework The Fluid 60c Calculate The True Fluid

oVtKtoV0dV AK dt, or V V e , where KV mh= = = Integrate again to find the displacement of the puck: tKto0Vx V dt [1 e ]K= = Apply to the particular case given: air, 1.8E5 kgms, m = 50 g, D = 9 cm, h = 0.12

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 1 Homework The Fluid Viscosity Then Given

Knowing for air at 20C from Table 1.4, estimate its viscosity at 500C by (a) the power-law, (b) the Sutherland law. Also make an estimate from (c) Figure 1.6. Compare with the accepted value 3.58E5 kg/m s. Solution 1.39 First change T from 500C

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 1 Homework Well Yes Indeed All Terms Have Dimensions

Therefore, to achieve dimensional homogeneity, we somehow must combine bending moment, whose dimensions are {ML2T2}, with area moment of inertia, {I} = {L4}, and end up with {ML2T2}. Well, it is clear that {I} contains neither mass {M} nor time {T} dimensions, but the bending moment contains both mass

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 10 Homework Consider The Flow In A Wide Channel Over A Bump

(a) We just need to determine the approach Froude number: 15.5 , water level will . .( )9.81(0.9)ooVFr Supercritical Ans agy= = = rise1.851 (b) We can find the Froude number over the bump from Eq. (10.39): 2 2 22 2 22322 2 2 2 12Finally(5.5) (5.5) (0.9)0.9 0.3

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 10 Homework Determine The Most Efficient Dimensions For A Clay

Problem 10.41 Determine the most efficient value of for the V-shaped channel of Fig. P10.41. Solution 10.41 Given the (simple) geometric properties 2A y cot ; P 2ycsc ; Eliminate y: P 2csc A tan =

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 10 Homework The Frictionless Profile Drops The Crest

Problem 10.106 A rectangular channel with n = 0.018 and a constant slope of 0.0025 increases its width linearly from b to 2b over a distance L, as in Fig. P10.106. (a) Determine the variation y(x) along the channel if b = 4 m, L =

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 10 Homework The Wave Causes A Change In Normal Froude Number

Solution 10.88* As with the oblique shock wave, the wave causes a change in normal Froude number. There is no change in Froude number parallel to the wave. 1/2 2 1/2 3/22 1 2 1 12 1/2211; 8 / [(1 8 ) 1]1[ 1 (1 8

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 10 Homework The Weir Discharge Must Equal This Flow

Problem 10.C1 February 1998 saw the failure of the earthen dam impounding California Jims Pond in southern Rhode Island. The resulting flood raised temporary havoc in the nearby village of Peace Dale. The pond is 17 acres in area and 15 ft deep and was full from heavy rains.

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 10 Homework Then The Flow Rate Manning’s Formula With

Solution 10.12 The velocity and flow rate were worked out in detail in Prob. 4.36: h0g sinx-Mom. yields u y(2h y), Q ubdy (a)2Ans.= = =3gbh sin3 2avg max h wide channel2

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 11 Homework Data Collected By The Author For Power Coefficient

When added to the plot shown below, all four data points seem to fit quite well. The data are useful for predicting general centrifugal-pump behavior and are well fit to either a 2nd-order polynomial or a single-term Power-law slightly less than parabolic: 2Q S S 21.914QS*Polynomial: C 1.97E 5N 2.58E

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 11 Homework Estimate The Best Efficiency Point And The Maximum

Q, gal/min: 0 400 800 1200 1600 2000 2400 , %: 0 32% 55% 70% 80% 85% 82% So maximum efficiency of 85% occurs at Q = 2000 gal/min. Ans. (a) (b) We dont know the values of QHP* * * or or C C C, but we can set

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 11 Homework Estimate The Maximum Discharge Possible

Problem 11.35 An 18-in-diameter centrifugal pump, running at 880 r/min with water at 20C, generates the following performance data: Q, gal/min: 0.0 2000 4000 6000 8000 10000 H, ft: 92 89 84 78 68 50 P, hp: 100 112 130 143 156 163 Determine (a) the

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 11 Homework Francis And Kaplan Turbines Are Often Provided

wheelwheel wheel best jet wheel1( )(1 cos )(0.8), , 16522jDPower Qu V u u V = = = wheel wheelrad3.2 m, solve for 28.5 ,s (a, b)If DPower Ans.= = ==rev272 min9.36 MW As shown on the figure below, which varies Dj, the optimum jet diameter is 34 cm,

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 11 Homework Kinetic And Potential Energy Changes Are Negligible

Solution 11.9 The following are observed: (a) The discharge Q is almost linearly proportional to speed and slightly less for the higher heads (H or p). (b) The efficiency (volumetric or overall) is nearly independent of speed and again slightly less for high p. (c) The power required is

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 11 Homework The Flow Enters About O Clock And Passes

Solution 11.86 Convert P* = 447 kW = 599 hp. Then, for D = 36 = 3.0 ft, 1/2 1/2sp 5/4 5/4nP 200(599)N (These are )H (30) Ans.= = 70 Francis turbines Use the given data to compute the dimensionless BEP coefficients: QP3 3 5205 599(550)**C ; C

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 11 Homework What Is The Maximum Achievable Flow Rate If You Use

Problem 11.C1 The net head of a little aquarium pump is given by the manufacturer as a function of volume flow rate as listed: Q, m3/s: 0 1.0E6 2.0E6 3.0E6 4.0E6 5.0E6 H, mm H2O: 1.10 1.00 0.80 0.60 0.35 0.0 What is the maximum achievable flow

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 2 Homework How Does Your Argument Change If There Is Seepage Under The Dam

The weight of the gate is (7.85)(6P2.4 lbf/ft3)(15 ft)(1/12 ft)(8 ft) = 4898 lbf. This weight acts downward at the CG of the full gate as shown (not the CG of the submerged portion). Thus, W is 7.5 ft above point B and has moment arm (7.5 cos 60 ft)

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 2 Homework If The Absolute Pressure At The Interface Between Water

Solution 2.14 The pressures at the three top surfaces must all be atmospheric, or zero gage pressure. Compute oil = (0.78)(9790) = 7636 N/m3. Also, from Table 2.1, water = 9790 N/m3 and mercury = 133100 N/m3 . The surface pressure equality is 123 3 3 3

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 2 Homework Manometer Liquid On The Reservoir Side Does Not Change Appreciably

Problem C2.1 Some manometers are constructed as in Fig. C2.1, where one side is a large reservoir (diameter D ) and the other side is a small tube of diameter d , open to the atmosphere. In such a case, the height of manometer liquid on the reservoir side

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 2 Homework Patients With Dangerous Hypertension Can Exhibit Systolic Pressures

Fig. P2.39 Problem 2.40 In Fig. P2.40, if pressure gage A reads 20 lbf/in2 absolute, find the pressure in the closed air space B. The manometer fluid is Meriam red oil, SG = 0.827

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 2 Homework The Can Weight Simply Equals The Weight Of The Displaced Water

Problem 2.101 The closed layered box in Fig. P2.101 has square horizontal cross-sections everywhere. All fluids are at 20C. Estimate the gage pressure of the air if (a) the hydrostatic force on panel AB is 48 kN; or if (b) the hydrostatic force on the bottom panel BC is

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 2 Homework The Horizontal Force Is Calculated From The Vertical Projection

Problem 2.84 Panel AB in Fig. P2.84 is a parabola with its maximum at point A . It is 150 cm wide into the paper. Neglect atmospheric pressure. Find (a) the vertical and (b) the horizontal water forces on the panel. Solution 2.84 (b) The

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 3 Homework At What Angular Velocity Is The Maximum Power Delivered

Solution 3.46 Let the CV enclose all three jets and the surface of the plate. Analyze the force and momentum balance tangential to the plate: t t 2 3 1F F 0 m V m ( V) m VcosmV (1 )m V m Vcos 0, solve for .Ans

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 3 Homework For A Control Volume Around The Cone

Solution 3.22 The mass flow is given by the throat conditions: 21 1 1 3284000 kg mm A V (0.01 m) 517 . (a)(287)(665) 4 smAns= = =kg0.0604 s For steady flow, this must equal the mass flow at the exit: 22 2 2 2 2kg

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 3 Homework The Case Of The Liquid Motion In A Frictionless U-tube

Solution 3.95 For water take = 998 kg/m3. The control volume surrounds the plate and yields (b) In 2 seconds, h drops from 1.63m to 1.58m, not much change. So, instead of a laborious calculus solution, find Qjet,av for an average depth hav =

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 3 Homework Use The Reynolds Transport Theorem Find Expression

Problem 3.C1 In a certain industrial process, oil of density flows through the inclined pipe in Fig. C3.1. A U-tube manometer with fluid density m, measures the pressure difference between points 1 and 2, as shown. The flow is steady, so that fluids in the U-tube are stationary.

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 3 Homework Water Flows Through A Circular Nozzle

( )2 2 2 21 2 1 2 2 11 0.79(998)Bernoulli, z z : p p V V 101000 [(41.4) (6.63) ]22= = + = + (b)Ans.760,000 Pa ( )2 2 2 21 2 1 2 2 11 0.79(998)Bernoulli, z z : p p V V 101000 [(41.4) (6.63) ]22=

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 3 Homework When Immersed In A Uniform Stream

Solution 3.71 From Prob. 3.50, recall that the essential data was Fig. P3.71 1 2 1 2V 250 m/s, V 900 m/s, m 151 kg/s, m 156 kg/s= = = = The CV should enclose the entire engine and also the deflector, cutting

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 4 Homework Integrate The Two Pressure Gradients Find The

(a) Substitute into the polar-coordinate equation of continuity, Eq. (4.12b): 21 1 1 1( ) (2 cos 2 ) ( 2 sin 2 ) 4cos 2 4cos 2 0 .( )rvr v r r Ans ar r r r r r + = + = Thus continuity is indeed

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 4 Homework Oil Flows Steadily Between Two Fixed Plates That

Fig. P4.86 2avg max2 dp hV u , where h plate half-width 4mm3 dx 3= = = = For SAE 10W oil, take = 870 kg/m3 and = 0.104 kg/ms. The manometer reads p = (Hg oil)gh = (13550 870)(9.81)(0.06) 7463 Pa for x = L = 1m 22p

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 4 Homework The Frequency Is Low Enough That At Any Given Time

Problem 4.C1 In a certain medical application, water at room temperature and pressure flows through a rectangular channel of length L = 10 cm, width s = 1.0 cm, and gap thickness b = 0.30 mm. The volume flow is sinusoidal, with amplitude Q = 0.50 mL/s and frequency

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 4 Homework What Could The Flow Represent Solution

22232 2 2 2max max12 4 416 u 16 ud T dT 4y(h 4hy 4y ), Integrate: h y 2hy Cdy 3dy kh kh= + = + + Before integrating again, note that dT/dy = 0 at y = h/2 (the symmetry condition), so C1 = h3/6. Now integrate once

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 4 Homework Water Flows Through A Two-dimensional Narrowing Wedge

Problem 4.71 Consider the following two-dimensional function f(x, y): (a) Under what conditions, if any, on (A,B,C,D) can this function be a steady, plane-flow velocity potential? (b) If you find a (x, y) to satisfy part (a), also find the associated stream function (x, y), if any, for

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 5 Homework Its Drag Simulated Long Model Pulled Tow

2(398 / )(0.05 ) 4.974/D rad s mU m s = = = Read the chart for 1. The writer reads 1 2.8. Thus we estimate the water lift force: 221(2.8)(998)(4) (0.8 )(0.05 ) 1788 .( )F U LD m m N N Ans b= = 1800

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 5 Homework Problem When The Fluid Exiting Nozzle

Problem 5.C1 Estimating pipe wall friction is one of the most common tasks in fluids engineering. For long circular, rough pipes in turbulent flow, wall shear w is a function of density , viscosity , average velocity V, pipe diameter d, and wall roughness height . Thus, functionally, we

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 5 Homework The Writer Chose The Following Two Use

This is a correct solution for Chapter 5, but in Chapter 8 we will use the official function, with extra factors of (1/2): 21/ 2( , )2()F D Lfcn UDU LD= This is a correct solution for Chapter 5, but in Chapter 8 we will use the official function, with

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 5 Homework Use Only The Quantities And Nondimensionalize And

Use only the quantities , E, and A to nondimensionalize y, x, and t, and rewrite the differential equation in dimensionless form. Do any parameters remain? Could they be removed by further manipulation of the variables? Solution 5.47 The appropriate dimensionless variables are y E xy* ; t*

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 6 Homework A Heat Exchanger Consists Of Multiple Parallel-plate Passages

Solution 6.96 For air at 20C and 1 atm, take = 1.20 kg/m3 and = 1.8E-5 kg/m-s. The hydraulic diameter of a square duct is easy, the side length a = 1 mm. The mass flow through one duct is 2131.5E 4

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 6 Homework For Pipe Find The Velocity And Reynolds

Solution 6.113 For water at 20C, take = 998 kg/m3 and = 0.001 kg/ms. For galvanized iron, = 0.15 mm. Assume turbulent flow, with p the same for each leg: 221 1 2 2f1 1 f2 m2 212L V V

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 6 Homework Increasing The Tube Diameter Would Lower Red

oilp/( g) 52200/[870(9.81)] 6.12 m = This is more than 3 m of oil, therefore it must include a friction loss: flow is up. Ans. (b) The energy equation between (1) and (2), with V1 = V2, gives 122 1 f f f 4pp 128 LQz z h , or

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 6 Homework Neglect Minor Losses Problem Water

This is ideal for Excel iteration: Guess f 0.020, get V 3.17 m/s, Red 316,000. Repeat: f 0.0138, get V 3.81 m/s, Red 380,000. Once more: f 0.01384, get V 3.805 m/s, Red 379,700. CONVERGED: V 3.805 m/s , Q = (/4)d2V = 0.030 m3/s. Writer verified! (b) Eq. (6.41)

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 6 Homework Solution Apply Steady Flow Energy Patm Atm

Problem 6.8 When water at 20C is in steady turbulent flow through an 8-cm-diameter pipe, the wall shear stress is 72 Pa. What is the axial pressure gradient ( p/ x) if the pipe is (a) horizontal; and (b) vertical with the flow up? Solution 6.8

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 6 Homework The Pitot-static Tube Formula Relates Velocity

Problem 6.C1 A Pitot-static probe will be used to measure the velocity distribution in a water tunnel at 20C. The two pressure lines from the probe will be connected to a U-tube manometer which uses a liquid of specific gravity 1.7. The maximum velocity expected in the water tunnel

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 6 Homework Through A Smooth Pipe From One Reservoir To A Lower One

smooth998(8.49)(0.05)Re 424000; f0.001= 0.0136 Write the energy equation between points (1) (the tank) and (2) (the open jet): 222pipe1f f pipeVp0 0 L V m10 80 h , where h f and V 8.49 g 2g g 2g d 2g s+ + = + + + = =21(8.49) 170Solve

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 7 Homework Ans Its Slight Slope But Low Drag Car

Solution 7.62 For sea-level air, take = 1.225 kg/m3 and = 1.78E5 kg/ms. Convert 90 mi/h = 40.2 m/s. We cannot compute Re without knowing the side length a, so we assume that Re > 1E4 and that Table 7.2 is valid. The worst case drag is when

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 7 Homework Assume Axisymmetric Flow That Is V And

Solution 7.13 The Navier-Stokes equations for cylindrical coordinates are given in Appendix D, with x in the Fig. P7.13 denoting the axial coordinate z. Assume axisymmetric flow, that is, v = 0 and / = 0 everywhere. The boundary layer assumptions are: Fig. P7.13 rrrvvuuv << u;

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 7 Homework Assume Constant Rolling Resistance For Automobile Mass

2clean0.00238F 421 1.19 (80.7) (6)(3) 587 lbf,2Power FV (b)Ans.= + =hp86 2clean0.00238F 421 1.19 (80.7) (6)(3) 587 lbf,2Power FV (b)Ans.= + =hp86 2 clean 0.00238 F 421 1.19 (80.7) (6)(3) 587 lbf, 2 Power FV (b)Ans. = + =hp86 Problem 7.89 The AMTRAK Acela train passes through Kingston, RI at 130 mi/h, scaring

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 7 Homework Atmospheric Boundary Layers Are Very Thick

Atmospheric boundary layers are very thick but follow formulas very similar to those of flat- plate theory. Consider wind blowing at 10 m/s at a height of 80 m above a smooth beach. Estimate the wind shear stress, in Pa, on the beach if the air is standard sea-level conditions. What

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 7 Homework Jane Wants To Estimate The Drag Coefficient Of Herself

Problem 7.C1 Jane wants to estimate the drag coefficient of herself on her bicycle. She measures the projected frontal area to be 0.40 m2 and the rolling resistance to be 0.80 N s/m. The mass of the bike is 15 kg, while the mass of Jane is 80 kg.

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 7 Homework Problem The Deep Submergence Vehicle Alvin

Solution 7.106 Since the only unknown is the kite area, this problem is simpler than Prob. P7.85. Convert 8 knots to 4.12 m/s. Assume sea level air density, a = 1.2255 kg/m3. For seawater, take = 1025 kg/m3 and = 0.00107 kg/m-s. The kite force balances the ship drag: 2

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 8 Homework After Timesteps Sec The Tabulated Velocities Below

Problem 8.C1 Did you know that you can solve simple fluid mechanics problems with Microsoft Excel? The successive relaxation technique for solving the Laplace equation for potential flow problems is easily set up on a spreadsheet, since the stream function at each interior cell is simply the average of

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 8 Homework Ans This Poisson’s Equation Looks Like The

Solution 8.104 For this two-dimensional polar-coordinate system, a differential mass is: 2 2 2 2rrel reldm br dr d , where b width into the paperSubtract off the stream U to

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 8 Homework Assume All Lift And Drag Due The

Problem 8.66* The inviscid velocity along the wedge in Prob. 8.65 has the analytic form U(x) = Cxm, where m = n 1 and n is the exponent in Eq. (8.53). Show that, for any C and n, computation of the laminar boundary layer by Thwaite's method, Eqs. (7.53)

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 8 Homework Fig Had Two Rotors High And

Problem 8.44 Suppose that circulation is added to the cylinder flow of Prob. 8.43 sufficient to place the stagnation points at = 35 and 145. What is the required vortex strength K in m2/s? Compute the resulting pressure and surface velocity at (a) the stagnation points, and (b)

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 8 Homework Pro B What Point The Hemisphere Should

Solution 8.90 Each configuration has a different advantage: (a) highly maneuverable but unstable, needs computer control; (b) maximum lift at low speeds, best for landing and take-off; (c) maximum speed possible with wings swept back. computer control; (b) maximum lift at low speeds, best for landing and take-off; (c)

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 8 Homework The Desired Angle Streamline Tan 1

This is only half a source. The equivalent source strength is m = 2(0.4m3/s) / [2(1m)] = 0.127 m2/s. Then, as in Fig. 8.9a, the stagnation point S is at a = m/U = (0.127 m2/s) / (1.2 m/s) = 0.106 m to the left of A. Ans. (a) The

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 9 Homework Compute The Mach Number Section

Air flows through a duct as in Fig. P9.84, where A1 = 24 cm2, A2 = 18 cm2, and A3 = 32 cm2. A normal shock stands at section 2. Compute (a) the mass flow, (b) the Mach number, and (c) the stagnation pressure at section 3. Solution 9.84

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 9 Homework Fig Estimate The Air Velocity Assuming

ocean). (c) Compute the speed of sound at 20C and 9000 atm and compare with the measured value of 2650 m/s (A. H. Smith and A. W. Lawson, J. Chem. Phys., vol. 22, 1954, p. 351). Solution 9.12 We may compute these values by differentiating Eq. (1.19) with

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 9 Homework Get The Mach Number In The Exit And Then Execute

Solution 9.146 (a) At the initial condition Ma1 = 2.0, from Table B.5 read 1 = 26.38. The first turn is 10, so 2 = 26.38 + 10 = 36.38. From Table B.5 read Ma2 = 2.38. For more accuracy, use Eq. (9.99) to obtain Ma2 = 2385.

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 9 Homework Now Need The Mach Number This Section

Solution 9.37 For a CV around the tank, write the mass and the energy equations: oooooppd d 0.6847A*mass: ( ) m, or B , where Bdt dt RT TR = = = ov o p oopdQ dW denergy: 0 c T mc Tdt dt dt RT+ = = +

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 9 Homework Solution Check The Mach Number Choked

Problem 9.60 When a pitot tube such as Fig. (6.30) is placed in a supersonic flow, a normal shock will stand in front of the probe. Suppose the probe reads po = 190 kPa and p = 150 kPa. If the stagnation temperature is 400 K, estimate the (supersonic)

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 9 Homework Solution Use Frictionless Heat Addition Theory

2 2 1 21222000( )(79.06) 63.25 ; Eq. (9.68 ) yields 0.0170* * 2500**At this , ( ) 2605, ( ) 4074 2605 1469(1469)(1.321)Finally, 2000 at 319,000 .( )0.00608p p p a Map p pfL fL f LMa henceD D Dp psia L m Ans a= = = =

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 9 Homework The Converging–diverging Nozzle Sketched In Fig

Problem 9.C1 The convergingdiverging nozzle sketched in Fig. C9.1 is designed to have a Mach number of 2.00 at the exit plane (assuming the flow remains nearly isentropic). The flow travels from tank a to tank b, where tank a is much larger than tank b. (a) Find the

Fluid Mechanics 8th Edition

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Aeronautical Engineering Chapter 9 Homework The Formula Is Quite Correct And Serves As An Interesting

Solution 9.131 The formula is quite correct and serves as an interesting alternative to Eq. (9.86). Notice that one can immediately solve for Ma1 if and are known, which would have been a great help in Prob. 9.124. For details of the proof, see page 371 of R. M.

Fluid Mechanics 8th Edition

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Fluid Mechanics 8th Edition

Trusted by Thousands ofStudents

Albert

Anna

Collins

Jill

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Karen

Hill

Rachel

Kristopher

Resources

Company

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Trusted by Thousands of
Students