Project_phase_2_2011 (2)

Project_phase_2_2011 - 1 Project description The project consists of two phases In each phase you perform a portion of the whole analysis and

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1. Project description The project consists of two phases. In each phase you perform a portion of the whole analysis and present your results in report. You will be handing in 2 separate reports, one for each phase. 2. The Givens The following design parameters and modeling information are known. Design Parameters for Aircraft Gross Weight of Airplane, W g lb 350000+1000* F g-force (Load Factor) # 2.5 Safety factor # 1.5 Type of Al alloy # Al 2024 Young’s modulus, E ksi 10,600 Poisson’s Ratio, ν 0.3 Yield strength ksi 50 The variable F involved in the calculation of gross weight is the first digit of your UFID. Design Parameters for Wing-box Wing-box Span, b in 1490+10* L Wing-box root section width, C WBroot in 170 Wing-box root section height, h r in 49 Wing-box root section flange thickness, t f in 1 Wing-box root section web thickness, t w in 0.5 Wing-box tip section width, C WBtip in 20 Wing-box tip section height in 10 Wing-box tip section thickness in 0.05 Sweep angle, degrees 30 The variable L involved in the calculation of span is the last digit of your UFID. Design Parameters for Wing Wing-root chord, C root in 337.25 Wing-tip chord, C tip in 90 Aspect Ratio, A r # 9.3 Wing Gross Area, S sq ft 3129
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Fig.1 The red lines shows the sweep of the wing-box section which you analyze Fig.2 Wing-box 3D model
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20” Fig.3 Wing-box top view Fig.4 Wing-box root section view 49” 170” 0.5” 1” A B C D 170” 745” (Half- span=b/2)
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Phase 2 Determination of the Von Mises stress, Factor of Safety and the Crack tip Stress Intensity Factor Report: 3 to 4 pages Due: 11/30/2011 Presentation slides. Description: Perform a shear flow analysis at the root section of the wing. Consider the shear flow due to V and the shear flow due to T at the wing root-section separately and superimpose the two. Refer to figure 5 for this phase of the project. The following steps are suggested for this phase: (a) To calculate the shear flows due to V approximate the wing root section as shown in Figure 5 to be made of concentrated areas placed so that the moment of inertia remains constant. (You can cut it open at point A if you are using that method to solve for closed sections) (b) To calculate the shear flow q T due to T use the resisting torque at the root section T root and use the formula ( 2 root T T q A = ) Fig. 5: Wing-root Section view to find shear flow
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This note was uploaded on 03/27/2012 for the course EAS 4200C taught by Professor Kim during the Fall '09 term at University of Florida.

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Project_phase_2_2011 - 1 Project description The project consists of two phases In each phase you perform a portion of the whole analysis and

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