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Rutgers - FINANCE - 390:300:03
.Chapter 11 Question 15a. Unrestrictedb. Temporarily restrictedc. Unrestricted if there is a reasonable expectation of eventual collectiond. Permanently restrictede. Unrestrictedf. Temporarily restrictedChapter 11 Question 171. Unrestricted, tempo
Rutgers - FINANCE - 390:300:03
Chapter 13Question 8Simonsen VillageBalance SheetGovernmental FundsAs of December 31, 2012DebtGeneralServiceAssetsCashReal estate taxes receivable, netState grants receivableDue from other fundsTotal assets$50,00040,000$36,000CapitalPro
Rutgers - FINANCE - 390:300:03
12.61st- accrual, modified accrual2nd - accrual12.71. Cash increases $1 million; Fund balance (net assets) increase $1 million revenue2.General FundAssets=Liabilities+Fund BalanceCash -800,000= Due to CPF +200,000- Transfer to CPF 1,000,000
Rutgers - FINANCE - 390:300:03
Chapter 14Case StudyMajor Medical CenterStatements of Financial PositionCommon Size RatiosDecember 31, 2012Percent$000sAssetsCurrent assets:Cash and cash equivalentsAssets limited as to useShort-term investmentsReceivables for patient care, n
Rutgers - FINANCE - 390:300:03
14-11.1.Indicates the relationship and discretionary funding of the national organization to itsaffiliates. These financial statements are those of the national organization, separatefrom the affiliates. However, we can see from the activity statement
Rutgers - FINANCE - 390:300:03
Chapter 10Question #15The Accounts Receivable, Net column could be split into two columns, one for Accounts Receivablewhich would have the beginning balance and transaction 8, and Allowance for Uncollectible Accounts whichwould have transaction 11. Th
Rutgers - FINANCE - 390:300:03
Chapter 10Question 17UnitsBeginning bal.Purchase Jan. 2Purchase July 1Price1,000300500$17$21$23ConsumptionFIFOLIFO1,000400200300500FIFOExpense$17,000$4,200$21,200LIFOExpense$6,800$6,300$11,500$24,600Balance LeftFIFOLIFO0
Rutgers - FINANCE - 390:300:03
Chapter 12Question 5Liabilities and Fund BalanceAssets=LiabilitiesRealFund Balance and Changes in Fund BalanceDue toEstateCashStateTaxesGrantsAccountsServiceDebtDeferredTaxSalariesFundReceivableReceivablePayableFundRevenuePayable
Rutgers - FINANCE - 390:300:03
Chapter 15Question 11Total current assetsTotal current liabilitiesCurrent ratioGovernmental Business Type$54,293,401$12,347,110$17,454,909$5,177,7163.112.38Total$66,640,511$22,632,6252.94Component$11,858,874$3,268,8823.63
Rutgers - FINANCE - 390:300:03
1-1Instructors Manual for Financial Management for Public, Health, and Not-for-Profit Organizations, 2EChapter 1INTRODUCTIONTOFINANCIALMANAGEMENTQuestions for Discussion1-1. Financial management is the subset of management that focuses on generati
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 1 Due Wednesday, August 24 at the beginning of class.Simple review problems. Show units throughout and work the problem in the system of units in which it is posed. 1. For a flow of air with density of 0.85 kilograms per cubi
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 1 SOLUTIONS Due Wednesday, August 24 at the beginning of class.Simple review problems. Show units throughout and work the problem in the system of units in which it is posed. 1. For a flow of air with density of 0.85 kilogram
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 2 Due Friday, August 26 at the beginning of class.Matlab review or introduction. Example 4.6 in the text is one example which we will take a close look at in a week. For now, we will prepare a plot to review or learn use of M
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 2 SOLUTIONDue Friday, August 26 at the beginning of class. Matlab review or introduction. Example 4.6 in the text is one example which we will take a close look at in a week. For now, we will prepare a plot to review or learn
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 3 Due Monday, August 29 at the beginning of class.Consider a pressure distribution near a leading edge of a symmetric airfoil. We will do this with the flow shown in Figure 3.22 of the text and solved on page 248. We will use
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 3 SOLUTION Due Monday, August 29 at the beginning of class.Consider a pressure distribution near a leading edge of a symmetric airfoil. We will do this with the flow shown in Figure 3.22 of the text and solved on page 248. We
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 4 Due Wednesday, August 31 at the beginning of class.Imagine that you are standing in line waiting to register early for a new third-semester aerodynamics course, AAE 335. There is a long line of your classmates in front of a
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 4Due Wednesday, August 31 at the beginning of class. Imagine that you are standing in line waiting to register early for a new third-semester aerodynamics course, AAE 335. There is a long line of your classmates in front of a
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 5 Due Friday, September 2 at the beginning of class.We find in section 4.7 that the distribution of vortex strength on the chord of the symmetric airfoil is: 1 + cos ( ) = 2V sin which can be non-dimensionalized, 1 + cos ( )
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 5Due Friday, September 2 at the beginning of class. We find in section 4.7 that the distribution of vortex strength on the chord of the symmetric airfoil is: ( ) = 2Vwhich can be non-dimensionalized,1 + cos sin ( ) 1 + c
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 6 Due Wednesday, September 7 at the beginning of class.In section 4.8 Anderson develops equation to determine chordwise position of the center of pressure, xcp . Similarly, he solves for the pitching moment coefficients about
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 6 SOLUTION(sign error in #1 and #2 and plot in #3 corrected)Due Wednesday, September 7 at the beginning of class. In section 4.8 Anderson develops equation to determine chordwise position of the center of pressure, xcp . Sim
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 7 Due Friday, September 9 at the beginning of class.The camber line, zc ( x ) , of a thin airfoil of chord length c is given by the piecewise continuous function: x x for 0 x 0.3c 0.2 0.6 - zc ( x ) c c = c 18 0.4 + x 0.6 - x
Purdue - AAE - 334
September 12 version final corrected version.AAE 334, Fall 2011, Homework 7 SOLUTIONDue Friday, September 9 at the beginning of class. The camber line, zc ( x ) , of a thin airfoil of chord length c is given by the piecewise continuous function: x x 0.
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 8 Due Monday, September 12 at the beginning of class.1. Show mathematically the effects of scaling airfoil camber on lift coefficient, quarterchord moment coefficient, and center of pressure at the same angle of attack? That
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 8 SOLUTIONDue Monday, September 12 at the beginning of class. 1. Show mathematically the effects of scaling airfoil camber on lift coefficient, quarter-chord moment coefficient, and center of pressure at the same angle of att
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 9 Due Wednesday, September 21 at the beginning of class.1. Solve for the induced velocity at points (x, y) in the flow below by adding up two semiinfinite vortices of equal strength, . Hint: no integration needed, just apply
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 9 SOLUTIONSDue Wednesday, September 21 at the beginning of class. 1. Solve for the induced velocity at points (x, y) in the flow below by adding up two semi-infinite vortices of equal strength, . Hint: no integration needed,
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 10 Due Friday, September 23 at the beginning of class.A horseshoe vortex of strength is used to model a lifting wing of span b for an airplane with performance of a 737-800. Specifically, b=34.3m and 270 m2 s 1 at speed of V
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 10 SOLUTIONS Due Friday, September 23 at the beginning of class.A horseshoe vortex of strength is used to model a lifting wing of span b for an airplane with performance of a 737-800. Specifically, b=34.3m and 270 m2 s 1 at s
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 11 Due Monday, September 26 at the beginning of class.1. Consider a single horseshoe vortex of span bi centered on the origin of the coordinate system, x, y 0,0 , in the z=0 plane as shown below in a view from above the wing.
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 11 SOLUTIONSDue Monday, September 26 at the beginning of class. 1. Consider a single horseshoe vortex of span bi centered on the origin of the coordinate system,x, y 0,0 , in the z=0 plane as shown below in a view from above
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 12 Due Wednesday, September 28 at the beginning of class.1. The first Boeing 787 is delivered to ANA today. It has a maximum takeoff weight of 502,500 pounds and a wing span of 197 feet. If we assume a take-off speed of 140 k
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 12 SOLUTIONS Due Wednesday, September 28 at the beginning of class.1. The first Boeing 787 is delivered to ANA today. It has a maximum takeoff weight of 502,500 pounds and a wing span of 197 feet. If we assume a take-off spee
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 13 Due Friday, September 30, at the beginning of class.1. Increasing the aspect ratio of a rectangular wing by increasing span while keeping chord, velocity, density, and lift force constant causes what change induced drag? S
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 13 Due Friday, September 30, at the beginning of class.1. Increasing the aspect ratio of a rectangular wing by increasing span while keeping chord, velocity, density, and lift force constant causes what change induced drag? S
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 14 Due Monday, October 3 at the beginning of class.Building on homework 11: Consider a single horseshoe vortex of span bi centered on the origin of the coordinate system, x, y 0,0 , in the z=0 plane as shown below in a view f
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 14 Due Monday, October 3 at the beginning of class.Building on homework 11: Consider a single horseshoe vortex of span system, isx, y 0,0 , in the z=0 plane as shown below in a view from above the wing.bicentered on the or
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 15 Due Monday, September 17, at the beginning of class.Work the problems in the system of units in which they are posed. Show units throughout your work for #2 through #4. No partial credit on such easy problems. 1. What is t
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 15 SOLUTIONSDue Monday, September 17, at the beginning of class. Work the problems in the system of units in which they are posed. Show units throughout your work for #2 through #4. No partial credit on such easy problems. 1.
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 16 Due Wednesday, September 19, at the beginning of class.We will see shortly that for compressible flow of an ideal gas, the ratio of stagnation (or total) pressure to static pressure is related to Mach number and gas proper
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 16 SOLUTION Due Wednesday, September 19, at the beginning of class.We will see shortly that for compressible flow of an ideal gas, the ratio of stagnation (or total) pressure to static pressure is related to Mach number and g
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 17 Due Monday, October 24, at the beginning of class.1. How fast must air at 70 Fahrenheit and 14.7 psi static pressure move for Bernoulli's equation to give a 10% error in total pressure? A supply tank for a supersonic wind
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 17 SOLUTION Due Monday, October 24, at the beginning of class.1. How fast must air at 70 Fahrenheit and 14.7 psi static pressure move for Bernoulli's equation to give a 10% error in total pressure? 1 1 p 2 1 p Bernoulli: po,
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 18 Due at beginning of lecture, Wednesday, October 26, 2011Consider the steady flow in the test section of a Mach 4 wind tunnel. The stagnation temperature is 20oC. For some optical diagnostic techniques, such as the Laser Di
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 18 SOLUTIONS Due at beginning of lecture, Wednesday, October 26, 2011Consider the steady flow in the test section of a Mach 4 wind tunnel. The stagnation temperature is 20oC. For some optical diagnostic techniques, such as th
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 19 Due at beginning of lecture, Friday, October 28, 2011A series of Matlab functions has been created to aid compressible flow students. They can be downloaded from Blackboard as one zipped file. A users guide is included in
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 19 SOLUTIONS Due at beginning of lecture, Friday, October 28, 2011A series of Matlab functions has been created to aid compressible flow students. They can be downloaded from Blackboard as one zipped file. A users guide is in
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 20 Due at beginning of lecture, Monday, October 31, 2011Consider a pitot-static probe in a supersonic flow. The streamline on centerline passes through a normal shock before stagnating isentropically. The streamline adjacent
Purdue - AAE - 334
AAE 334, Fall 2011, Homework 20 SOLUTIONS Due at beginning of lecture, Monday, October 31, 2011Consider a pitot-static probe in a supersonic flow. The streamline on centerline passes through a normal shock before stagnating isentropically. The streamline
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 21 Due Wednesday, November 2 at the beginning of class. We wish to find the value of upstream Mach number for which the downstream Mach number is one half of the upstream Mach number. Perform this work numerically: 1. Use the f
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 21 SOLUTIONS Due Wednesday, November 2 at the beginning of class. We wish to find the value of upstream Mach number for which the downstream Mach number is one half of the upstream Mach number. Perform this work numerically: 1.
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 22 Due Friday, November 4 at the beginning of class. In lecture and Chapter 9 we are learning that the static thermodynamics through a steady oblique shock are the same formulae as for the steady normal shock if we use the upst
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 22 SOLUTIONSDue Friday, November 4 at the beginning of class. In lecture and Chapter 9 we are learning that the static thermodynamics through a steady oblique shock are the same formulae as for the steady normal shock if we us
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 23 Due Monday, November 7 at the beginning of class. The oblique shock chart in the test is difficult to read at times. You can create your own quite simply with use of the Matlab routines supplied on Blackboard this semester.
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 23 SOLUTIONDue Monday, November 7 at the beginning of class. The oblique shock chart in the test is difficult to read at times. You can create your own quite simply with use of the Matlab routines supplied on Blackboard this s
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 24 Due Wednesday, November 9 at the beginning of class. 1. Using an oblique shock chart, answer these questions: a. What is the turning angle in degrees for an upstream Mach number of 2 and a wave angle of 40 degrees? b. What i
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 24 SOLUTIONS Due Wednesday, November 9 at the beginning of class. 1. Using an oblique shock chart, answer these questions: a. What is the turning angle in degrees for an upstream Mach number of 2 and a wave angle of 40 degrees?
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 25 Due Wednesday, November 16 at the beginning of class. 1. Compute manually (not using the PM_ Matlab functions) the pressure after a 10 degree expansion corner if the upstream flow is at Mach 2 and pressure of 100 kPa. T 2. C
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 25 SOLUTIONS Due Wednesday, November 16 at the beginning of class. 1. Compute manually (not using the PM_ Matlab functions) the pressure after a 10 degree expansion corner if the upstream flow is at Mach 2 and pressure of 100 k
Purdue - AAE - 334
AAE 334 Fall 2011, Homework 26 Due Friday, November 18 at the beginning of class. Use the shock-expansion method to compute the lift and drag coefficients for the airfoil sketched below in a Mach 1.8 flow. Chord length is c and maximum thickness is at the