torsion of a racing car aerofoil.

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An aerofoil is manufacturing from a carbon fibre reinforced polymer skin thickness 1.5mm with the geometry, lengths and areas given in the accompanying assignment XL spread sheet containing a corresponding SET No. ranging from 1 to 14.

Torsion of a racing car aerofoil. An aerofoil is manufacturing from a carbon fibre reinforced polymer skin thickness 1.5mm with the geometry, lengths and areas given in the accompanying assignment XL spread sheet containing a corresponding SET No. ranging from 1 to 14. use SET No 6. A schematic of the cross-section is shown in fig A1. Using this information complete the following tasks stated below and answer the questions at the end of the tasks. Position Length (mm) AB BC CD DE EF FG GH HA CG Area Size (mm2) ABH BCGH CDFG DEF Table A1, for your actual lengths and areas see your set number in the spreadsheet at the appendix. B C D A E H G F Fig A1 Schematic Cross-section of the aerofoil Assume for the skin the following properties, Mean E fibre = 350 GPa, volume fraction = 65%, design strain 0.5%, and effective length is 1.6m. Task 1 (40%) Assuming the car can achieve a maximum speed of 220 mph with a lift coefficient of 1.6 for the aerofoil and the centre of twist is approximately is 15% of the chord length AE; determine the maximum angle of twist and shear stress induced in the aerofoil for this case. Task 2 (10%) The actual aerofoil however has closed ends with a small plate of the same material. Estimate how this will change your predicted answer and indicate the positions along the length were this is most affected using a simple sketch. Task 3 (25%) If under race condition the section is subject to an impact at the mid-point between the end plates which damages section FG. Estimate the increase in angle of twist and the maximum induced shear stress due this impact. Supplementary questions 1. If the aerofoil was manufactured from aluminium comment on how the behaviour of the aerofoil would react to the conditions in tasks 1 to 3 inclusive (10%) 2. Describe how the “centre of twist” affects the loading (5%) 3. Describe briefly how the composite part would be joined and how you could estimate the stress in the adhesive. (10%) LOs for this work are as follows: Demonstrate a comprehensive understanding of the scientific principles of mechanical and related engineering disciplines (US1m Demonstrate an awareness of developing technologies related to mechanical engineering. (US4m) Submission method On completion of your task you will need to upload your solution via the moodle link provided by your module tutors. Appendix Position Length(mm) DIMENSIONS Area AB 78 ABH BC 86 CD Size (mm2) Area 960 AB BCGH 2700 BC 83 BCGH 2685 60 CDFG 2300 CD 57 CDFG 2285 DE 38 DEF 160 DE 35 DEF EF 38 EF 35 FG 64 FG 61 GH 92 HA 80 GH 89 HA 77 CG 36 CG 33 AB BC CD DE EF FG GH HA CG 82 90 64 42 42 68 96 84 40 ABH BCGH CDFG DEF AB 86 ABH BC SET 1 75 945 145 SET 5 AB BC CD DE EF FG GH HA CG 72 80 54 32 32 58 86 74 30 ABH BCGH CDFG DEF 991 AB 68 ABH 2731 BC 76 BCGH 2658 2331 CD 50 CDFG 2258 191 DE 28 DEF 28 976 2716 2316 176 SET 2 94 BCGH CD 68 CDFG DE 46 DEF EF 46 EF FG 72 FG GH 100 HA 88 54 GH 82 HA 70 CG 44 CG 26 SET 3 ABH Size (mm2) 930 2670 2270 130 SET 6 SET 7 The grading system and assessment criteria are those as described in the module handbook in sections 11, 13 and 14. 918 118

Tutor Answer

DaveDance
School: University of Virginia

Attached.

Task 1.
Mean E fibre=350 GPa
Effective length =1.6m
Lift coefficient =1.6
Chord=28mm+50mm+76mm+68mm
=222mm.
a)Shear:
Shear=QV/Ib

(i) Centroid of beam function
=(Aiyi/Ai) +(A2y2/A2) +.... +(AnYn/An)
={(918*1,628)+(2658*1.572) +(2258*1.522)+(118*1.446)} /5952
=9284.184/5952
=1.55984274m
(ii) Statical moment
=5.952*1.6

1|Page

=9.5392
(iii)Moment of inertia
={(Ii+Aid²) +(I2+A2d²)+..... +In+An(d²)}
I=0.222*0.26
=0.005792
A=918+2658+2258+118
=5952
d=0.02...

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