AE 6070 4070 Quiz I Fall 2006 Due on October 17 2006 1 AE 4070 6070 Students You are asked to design a rotor that will carry 15000 lbf at 4000 feet pressure altitude at 95 deg F Due to geometric limitations the rotor diameter is 43 feet The designer decides to use a thrust weighted solidity of 0 1 and has chosen the number of blades to be 4 The designer also decides to use a 3 bladed rotor for this design Because the company has prior experience with NACA 0012 airfoils a NACA0012 airfoil is also chosen The tip speed is selected to be 650 feet sec Determine the best combinations of linear taper ratio and linear twist that will minimize power consumption Use combined Blade Element Momentum theory and Prandtl s tip loss model F r The NACA 0012 airfoil properties are supplied below as a table of alpha and Mach number Please use these 2 AE 6070 students only The designer seeks your advice on changing solidity between 0 05 0 075 or 0 10 and the number of blades between 2 3 4 or 5 Repeat the BEMT simulations for subsets of these combinations and give your recommendation Note that a very small value of sigma may cause the rotor to stall NACA 0012 Standard C81 Table CL M alpha 0 0 2 0 3 0 4 0 5 0 6 0 7 0 75 0 8 0 9 1 180 0 0 0 0 0 0 0 0 0 0 0 172 5 0 78 0 78 0 78 0 78 0 78 0 78 0 78 0 78 0 78 0 78 0 78 161 0 62 0 62 0 62 0 62 0 62 0 62 0 62 0 62 0 62 0 62 0 62 147 1 1 1 1 1 1 1 1 1 1 1 129 1 1 1 1 1 1 1 1 1 1 1 49 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 39 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 21 0 8 0 8 0 81 0 83 0 85 0 85 0 85 0 71 0 68 0 64 0 64 16 5 1 007 1 007 0 944 0 96 0 965 0 965 0 965 0 795 0 76 0 7 0 7 15 1 19 1 19 1 09 1 055 0 99 0 98 0 98 0 83 0 79 0 72 0 72 14 1 333 1 333 1 22 1 096 1 0 97 0 97 0 84 0 805 0 73 0 73 13 1 334 1 334 1 28 1 12 1 0 96 0 96 0 85 0 815 0 735 0 735 12 1 255 1 255 1 26 1 13 1 0 947 0 94 0 85 0 82 0 74 0 74 11 1 161 1 161 1 19 1 12 0 994 0 93 0 923 0 85 0 81 0 74 0 74 10 1 055 1 055 1 01 1 082 0 985 0 91 0 9 0 845 0 805 0 73 0 73 8 0 844 0 844 0 88 0 907 0 922 0 87 0 84 0 82 0 77 0 695 0 695 6 0 633 0 633 0 66 0 684 0 741 0 77 0 75 0 77 0 72 0 593 0 593 4 0 422 0 422 0 44 0 456 0 494 0 544 0 578 0 627 0 603 0 396 0 396 CD 2 0 211 0 211 0 22 0 228 0 247 0 272 0 313 0 35 0 395 0 2 0 2 0 0 0 0 0 0 0 0 0 0 0 0 2 0 211 0 211 0 22 0 228 0 247 0 272 0 313 0 35 0 395 0 2 0 2 4 0 422 0 422 0 44 0 456 0 494 0 544 0 578 0 627 0 603 0 396 0 396 6 0 633 0 633 0 66 0 684 0 741 0 77 0 75 0 77 0 72 0 593 0 593 8 0 844 0 844 0 88 0 907 0 922 0 87 0 84 0 82 0 77 0 695 0 695 10 1 055 1 055 1 1 1 082 0 985 0 91 0 9 0 845 0 805 0 73 0 73 11 1 161 1 161 1 19 1 12 0 994 0 93 0 923 0 85 0 81 0 74 0 74 12 1 255 1 255 1 26 1 13 1 0 947 0 94 0 85 0 82 0 74 0 74 13 1 334 1 334 1 28 1 12 1 0 96 0 96 0 85 0 815 0 735 0 735 14 1 333 1 333 1 22 1 096 1 0 97 0 97 0 84 0 805 0 73 0 73 15 1 19 1 19 1 09 1 055 0 99 0 98 0 98 0 83 0 79 0 73 0 73 16 5 1 007 1 007 0 944 0 96 0 965 0 965 0 965 0 795 0 76 0 7 0 7 21 0 8 0 8 0 81 0 83 0 85 0 85 0 85 0 71 0 68 0 64 0 64 39 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 49 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 1 18 129 1 1 1 1 1 1 1 1 1 1 1 147 1 1 1 1 1 1 1 1 1 1 1 161 0 62 0 62 0 62 0 62 0 62 0 62 0 62 0 62 0 62 0 62 0 62 172 5 0 78 0 78 0 78 0 78 0 78 0 78 0 78 0 78 0 78 0 78 0 78 180 0 0 0 0 0 0 0 0 0 0 0 M alpha 0 0 18 0 28 0 38 0 48 0 62 0 72 0 77 0 82 0 92 1 180 0 022 0 022 0 022 0 022 0 022 0 022 0 022 0 022 0 022 0 022 0 022 175 0 062 0 062 0 062 0 062 0 062 0 062 0 062 0 062 0 062 0 062 0 062 170 0 132 0 132 0 132 0 132 0 132 0 132 0 132 0 132 0 132 0 132 0 132 165 0 242 0 242 0 242 0 242 0 242 0 242 0 242 0 242 0 242 0 242 0 242 160 0 302 0 302 0 302 0 302 0 302 0 302 0 302 0 302 0 302 0 302 0 …