Massachusetts Institute of Technology Department of Aeronautics and Astronautics Cambridge, MA 02139 16.01/16.02 Unified Engineering I, II Fall 2003 Problem Set 14 Name: Due Date: 12/9/03 Time Spent (min) F18 F19 F20 M19 M20 M21 M22 U4 Study Time Announcements:� � Unified Engineering Fall 2003 Fluids Problems F18-20 √ F18. Wind with velocity V∞ is flowing over a mountain ridge have the shape Y (x)= Cx. The flow is to be modeled by superimposing a uniform flow with a source located at some location x, y =(d, 0). ψ(x, y)= V∞y + Λln(x − d)2 + y 2 4π x y d V r θ Λ a) Determine both the source’s location d, and the strength Λ, with the conditions: u =0 at x, y =(0, 0)√ v/u = dY /dx at x, y =(d, Cd) The second condition simply requires that the flow direction on the ridge surface directly above the source is parallel to the ridge surface. b) A sailplane flying in the slope lift upwind of the ridge requires a vertical velocity of at least v ≥ 1m/s tostay aloft. For awind speed of V∞ = 15m/s (33 mph) and ridge size scale C = 500m, determine the maximum flyable radius r(θ) inside which the sailplane can sustain flight. Plot the r(θ) boundary superimposed on a plot of the ridge. F19. Determine the Cp variation along the −x and +y directions for a) Freestream V∞ with source of strength Λ b) Freestream V∞ with vortex of strength Γ c) Freestream V∞ with doublet of strength κ. At large distances, where does a lifting airfoil cause the strongest disturbance to the flow (as measured by Cp), above and below, or fore and aft? Explain. F20. Two very long source panels of strength ±λ are located at distance h apart. Determine the velocities at points A, B, C. C +λ h B −λ AUnified Engineering Fall 2003 Problem M19 Silicon carbide fiber reinforced titanium matrix composites are being considered for use in the compressor stages of next generation gas turbine engines. It is required to obtain the elastic properties of a batch of material under development. To do this, two test specimens are machined from the batch, each 200 mm long and 10 mm by 10 mm in width and thickness. Two strain gauges are attached to specimens (i) in which the load is applied parallel to the fiber direction and three are applied to specimen (ii) which is loaded perpendicular to the fiber direction as shown below. A uniaxial load, P is applied through a mechanical testing machine, which is varied from 0 to 14 kN. a) What is the fewest number of independent engineering elastic constants that you would expect to be required to describe the elastic constitutive behavior of this material?. State any assumptions that you are making in giving this number.Strain (microstrain) Test (i) Specimen (ii)600 800 gauge b gauge a Gauge c Gauge d Gauge f 500 600 400 300 200 100 Strain (microstrain)400 200 0 0 -200 -100 -200 -400 0 5 10 15 0 5 10 15 Load (kN) Load (kN) b) The graphs above show the strain readings plotted vs. applied load for the two tests. Using the information contained in the graphs calculate all the engineering elastic constants that you can obtain. If there are any elastic constants that you cannot obtain/estimate from this data suggest additional tests that you might perform in order to obtain them. In describing the elastic constants use x, y and z to indicate the orthogonal material directions, with x aligned parallel to the fibers. c) Estimate the fiber volume fraction for this composite, given that the Young’s modulus of SiC is 450 GPa, and the Poisson’s ratio is 0.16 and the corresponding values for the titanium alloy used for a matrix are 110 GPa and 0.34 respectively. Is this consistent with the data provided? 2Problem M20 A 45° strain gauge rosette attached to the surface of an aluminum alloy wing skin panel measures the following strains: ea = -0.0025, eb=0.0020, ec=-0.0040 The orientation of the gauges is shown below a b c a) What are the extensional stresses in the a, b and c directions? b) What are the in-plane principal stresses? The Young's modulus of the aluminum alloy is 70 GPa, the Poisson's ratio is 0.33 (note. the a, b, and c directions are numbered in the counterclockwise direction) 3Problem M21 a) A tensile specimen is made of an epoxy (a thermosetting polymer). It is loaded in the z direction to a stress of 100 MPa. Assuming that the epoxy remains elastic, what are the resulting strains in the x, y and z directions? The Young's modulus of the epoxy is 3 GPa and the Poisson's ratio is 0.3 b) A thin (t<<R) layer of an epoxy adhesive is used to join two silicon carbide bars of circular cross-section, as shown below. An axial (z direction) tensile stress of 100 MPa is applied to the joint as shown. Calculate the axial strain (ezz) in the adhesive. The Young's modulus of the epoxy adhesive is 2 GPa, the Poisson's ratio is 0.3. The Young's modulus of the SiC is 450 GPa and the Poisson's ratio is 0.16. State any assumptions/approximations that you make in solving this problem - note that you may not be able to achieve an exact solution but you should aim to obtain a good approximation. Hint: think about the transverse strains in the adhesive (e and eyy ).xx 100 MPa 100 MPa 2R Adhesive SiC x y z t 100 MPa 100 MPa Perspective View Cross-Section 4Problem M22 A cantilever beam is to be made with a length L and circular cross section, radius R (to be specified by the designer), to support an applied moment, M. a) What combination of material properties must be minimized to obtain the highest bending stiffness (i.e. minimum deflection for a given applied moment) beam for a given mass of material? (show your working). The deflection, d, of a cantilever beam of this shape is given by: 2ML2 d= pR4E where E is the Young's modulus. b) Choose between the following material choices to select the most promising material to construct a wing for a small Unmanned Aerial Vehicle (which will carry load as a cantilever beam) Material Density, r, Modulus, E, Poisson’s Yield Stress, Price , p, (Mg/m3) (GPa) Ratio sy, (MPa) ($/Mg) Mild Steel 7.9 203 0.31 220 375 Aluminum alloy (2024) 2.8 71 0.33 350 1650 Titanium alloy Ti-6Al4V 4.5 120 0.34 850 30000 Carbon fiber composite 1.5 230 0.3 1050 70000 Polyethelene (High Density) 0.96 1.1 0.39 30 1000 Wood (pine) 0.6 12 0.35 300 300 Silicon Carbide (SiC) 3.0 410 0.17 300 (Flexural) 30000 c) To a first approximation the human hip joint
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