Acoustics and Noise Control

Aerodynamics and Heat Transfer

Aerospace Design and Practice

Aerospace Materials

Aerospace Propulsion

Aerospace Systems Design

Aerospace Vehicle Performance

Aircraft Stability and Control

Composite Materials

Introductory Aeroelasticity

Lightweight Structures

ffi Carleton l(F uNrvERsrrY ,9'r" ^ f FINAL EXAMINATION December 2008 DURATION: 3 HOURS No.of Students: 57 A Department Name & Mechanical & Aerospace Engineering AERO 4302'_ MECH 5000 F Course Number: Gourse lnstructor(s): M. I. Yaras THORIZED MEMORANDA openbooks and notes, calculator Students MUST count the number of pages in this examination questionpaper beforebeginning to write, and report any discrepancy immediatelyto a proctor. This question paper has 4 pages. This examinationquestion MAy be taken from the examination room. Answer all 4 questions. They are of equalvalue. 1. A ceilingfan consisls of five blades of 0.8m length and 0.1m width, which rotate at l00rpm. Estimate the torque needed to overcome the friction on the blades if they canbe appro^ximated to act as flat plates operating in laminar, steady state conditions (p:1.2 kg/m3, v:1 .5x l0-5 m2ls;. 2. A line source of strength m in a two-dimensional flow is located at the point y--a, x:0, above a solid planewall aty:9. In addition to the line source, there exists a steady uniform flow U in the x direction.Determine expressions for: a) the stream function V6,il of this flow; b) the velocity u(x) at the wall; c) the static pressure p(x) at the wall. 3. Assumingthat the velocity profile in a laminar boundary layer of thickness dis given by: where a is the velocity at distance y from the surface , and (J" is the freestream velocitv. demonstrate that u ^( v\ (v)' Lt - | -t - | u " \.d/ \.d/ AERO 4302 /MECH 5OOO Irinal}lxamination December 2008 4v 3l u"6 c/ 5 420 4- Two immiscible liquids A and B areflowing steadily and in laminar state down an inclined surface. A two-dimensional boundary layerdevelops on the surface andgrows to approach the free surface. Derive the momentumintegralequation for this boundary layer. //4 c/ I 0oa AERO4302 /MECH 500() Final Examination December 2008 The following three questions are to be answered ONLY by students registered in MECH 5000. The students are to work on these questions independentlv during the Z4-hourperiod following the 3-hour in-class examination, and submit their answers to the course instructor by 8:30 AM on Dec.17 (location: 3135ME). The questions areof equal value, and will constitute 30% of the final--exam mark for the students registered in MECH 5000. 5. The figurebelow illustrates a two-dimensionaljet entering a reservoir which contains stationary fluid. A solution is sought to the laminarboundary-layer equations for this situation. Assumingthat thereis no pressure gradient alongthe jet, we arelooking for a similarity solution for the stream function of the following form: v@, y) = 6avxt't f (r/) where rl=d+ x-' In the above expressions, cr is a dimensional constant andv is the kinematic viscosity of the fluid. Confirm the validity of this stream function.Derive the differentialequation for the function f(n) and the boundary conditions which haveto be satisfied. ,cl "ntcrut r tBmir.

AERO | 4302 | Aerodynamics and Heat Transfer | exam | ffi Carleton l(F uNrvERsrrY  9

Exam-AERO4306-2005December.pdf-D,f. ~ Mechanical & Aerospace Engineering

'.. "". """"""'1' -~ ' , " -, \~ . .Mechanical and Aerospace Engineering AERO 3700 4 Final Exam, December 2002 9.. A band of polyisoprene is to be used to hold a bundle of aluminum rods for a period of one year.. If the stress in the band is less than 10..5 MPa, the rods will not be held tightly enough for safety.. Tests show that an initial stress of7 MPa decreases to 6..86 MPa over a 42 day period.. a. What is the name given to the observedphenomenon? What is happening during the observed phenomenon? b.. Estimate the stressthat must be must be applied to the polyisoprene band at the time if application if it must stay above 10.5 MPa for a full year. 10. A number of videos were presentedduring class. a. List four videos that were shown.. A general description is sufficient if you can't remember the exact name.. b. Describe the method of pultrusion of composites that was shown in the Tooling for Composite video. \ ,/' / ~/ ~,.. . ~i . III_I~~j ~ - 0 '.'.'c -c ."'~i\c1i' ',,:,i.{~ \ r -., ~ ."'> . .Mechanical and Aerospace Engineering AERO 3700 5 Final Exam, December 2002 THIS PAGE MUST BE HANDED IN WITH YOUR EXAM BOOKLET Table 1 Aluminum Data for Question 4. Sample Condition Yield Strength -Tensile Strength -% Elongation 1060 Al 0 1060 Al HI8 5052 Al HI8 ;"~7~ --~.~.- i~/!-"-~;~.,-c .;_c:,-~' " .::" ] .~, ,-'~-":;::A.J... ~;"'- , ~~ -'~ ~ .- f. .~:r~ '"..,~~;(. . fstimate temperatures I Figure 1 for Question 8 Fp ..c'" -.,! c ' I ."', } ! .-.'-"! , Fbh j. Fbh ~ ! J ~ i -.l l i Ii 'l~ ~ J r' "'~:;;-=::'::r:::':':'~:-::-J ' .I! : .I ,_:.-:-. .L- 1 ! v Figure 2 for Question 8 ~ ~' :r.~ . Engineering 87.370*A 6 ~ Final Exam December 2002 ... £ = C~exp-QIRT S = Ee 0'" 1 't = Gy R = -L -= C e -QIRT Eo. 't I-I elongation = .L!!-xl00 -0'1 --(rL + 2r45 + rT) I R-- r- 0 Eo. 4 A -A reduction in area = --!!-1 x 100 ( 2 ) A Gb r L + r T -r 45 0 't cx -L1r = C I 2 P S=- E Ao G = B = In(wlw ) 2(1 +v) W 0 L11 e=- I 0' 0 P =2 e = In (tit) I p to. P 0'=- E A PI=- B , =ln(lll) p 0 i I ) 2/3 B = 1 -O'y I PI = -r = BIl//Bt 0 P 0' = KBn 0' = M't P = ~ VP. y C C L..,II B = n 11 't := 0'/2 E =E I" +EI" y y C mlm ,Jr B =B +B. +B +B total elastic plastic thermal creep k 0' =0' +- -Y 0 {D eth -o.L1T 1 -1m Ir ---+- E .J. E E C m r Kl = O'Y{Xa ( 2 ) F = Y nr2 1 + ~ f 3h ~ = C(L1K)m dN 0' = kEn Em ac da 0' = 0' e -tit N = [C(~~ R = 1.~87 ~- = 8.314 --~ (} mole K mole k

AERO | 3700 | Aerospace Materials | exam | '.. "". """"""'1' -~ '   " -  

DUMTION: CARLETON UNIVERSITY Mid-Term EXAMINATION February 2005 HOURS No. of Students: 35 Course Number: Mechanical and Aerospace Engineering AERO 3101 Prof. C.L.Tan Department Name & Course Instructor(s): agesinthisexaminationquestionpaperbeforebe9inningto write,and report any discrepancy immediately to a proctor- This question paperhas 7 pages' Thisexamination question paper MAY NOT be takenfrom the examination room AUTHORIZED MEMORANDA Course notes and calculatoronlY NOTE: 1. Answer any TWO questions. 2. All questions carry equal marks. Name: StudentNumber: Page2 AERO3 I 0l Lightweight Structures Mid-Term Examination February 2005 1. Using the unit load method, determine the deflection of the spring under the vertical force Q actingat the tip of the cantilever as shown in the figure' The flexural rigidity of the ,EI beam isEl and the spring constant r:7' AERO3 101Lightweight Structures Mid_Term Examination Februarv 2005 Page 3 AERO31 01 Lightweight Structures Mid-TermExamination Februarv 2005 Page4 2. A propped-up cantilever beam AB is subjected to a distributed load which varies from zsro at A to w, in intensity at B, as shown in the figure- Assuming that the transverse deflection, v, varies accordi.g to v : a f (x - Z/, determinethe approximate solution for the maximum deflection of the beamusing the Rayleigh-Ritz method. AERO3 101 Lightweight Structures Mid-Term fxamination February 2005 Page 5 AERO3 I 0l Ligbtweight Structures Mid-Term Examination Februarv 2005 Page6 3. A beam section, idealisedas a sheet-stringer construction,is subjected to a vertical force V: l0 kN through its shearcentre O, as shown in the figure. The effective areas of the stringersare all equal in value. Determine: a) the internal forces in the stringers; b) the shearflows in the webs; and c) the value of e" Stri nger 2I AERO3 1 01 Lightweight Structures Mid-Term Examination Februarv 2005 PageT

All courses in AERO

Popular Documents