3D Design

3D Design

Error: Duplicate Coordinates found in Coordinates File

    • Ryan Hirani
      Subscriber

      Hello, I am having trouble importing a .dat file for airfoil coordinates. When I enter the last coordinate as 1 0, it provides the error of duplicate coordinates and when I remove that duplicate coordinate, the shape is now not closed and I am unable to form a surface. 

       

      Any help is truly appreciated! 

    • Ryan Hirani
      Subscriber

      Dat file contents below - 

      1 1 1.000000    0.000000 0
      1 2 0.950000    0.005404 0
      1 3 0.900000    0.010633 0
      1 4 0.850000    0.015830 0
      1 5 0.800000    0.021023 0
      1 6 0.750000    0.026205 0
      1 7 0.700000    0.031242 0
      1 8 0.650000    0.035967 0
      1 9 0.600000    0.040210 0
      1 10 0.550000    0.043868 0
      1 11 0.500000    0.046834 0
      1 12 0.450000    0.048931 0
      1 13 0.400000    0.049954 0
      1 14 0.350000    0.049681 0
      1 15 0.300000    0.048369 0
      1 16 0.250000    0.046079 0
      1 17 0.200000    0.042737 0
      1 18 0.180000    0.041065 0
      1 19 0.160000    0.039182 0
      1 20 0.140000    0.037073 0
      1 21 0.120000    0.034705 0
      1 22 0.100000    0.032014 0
      1 23 0.090000    0.030520 0
      1 24 0.080000    0.028920 0
      1 25 0.070000    0.027203 0
      1 26 0.060000    0.025347 0
      1 27 0.050000    0.023310 0
      1 28 0.040000    0.021031 0
      1 29 0.030000    0.018420 0
      1 30 0.020000    0.015294 0
      1 31 0.010000    0.011167 0
      1 32 0.009500    0.010911 0
      1 33 0.009000    0.010648 0
      1 34 0.008500    0.010375 0
      1 35 0.008000    0.010095 0
      1 36 0.007500    0.009803 0
      1 37 0.007000    0.009502 0
      1 38 0.006500    0.009187 0
      1 39 0.006000    0.008859 0
      1 40 0.005500    0.008513 0
      1 41 0.005000    0.008149 0
      1 42 0.004500    0.007760 0
      1 43 0.004000    0.007346 0
      1 44 0.003500    0.006901 0
      1 45 0.003000    0.006415 0
      1 46 0.002500    0.005880 0
      1 47 0.002250    0.005592 0
      1 48 0.002000    0.005282 0
      1 49 0.001750    0.004953 0
      1 50 0.001500    0.004594 0
      1 51 0.001250    0.004205 0
      1 52 0.001000    0.003766 0
      1 53 0.000750    0.003269 0
      1 54 0.000500    0.002677 0
      1 55 0.000250    0.001890 0
      1 56 0.000000    0.000000 0
      1 57 0.000250    -0.001890 0
      1 58 0.000500    -0.002677 0
      1 59 0.000750    -0.003269 0
      1 60 0.001000    -0.003766 0
      1 61 0.001250    -0.004205 0
      1 62 0.001500    -0.004594 0
      1 63 0.001750    -0.004953 0
      1 64 0.002000    -0.005282 0
      1 65 0.002250    -0.005592 0
      1 66 0.002500    -0.005880 0
      1 67 0.003000    -0.006415 0
      1 68 0.003500    -0.006901 0
      1 69 0.004000    -0.007346 0
      1 70 0.004500    -0.007760 0
      1 71 0.005000    -0.008149 0
      1 72 0.005500    -0.008513 0
      1 73 0.006000    -0.008859 0
      1 74 0.006500    -0.009187 0
      1 75 0.007000    -0.009502 0
      1 76 0.007500    -0.009803 0
      1 77 0.008000    -0.010095 0
      1 78 0.008500    -0.010375 0
      1 79 0.009000    -0.010648 0
      1 80 0.009500    -0.010911 0
      1 81 0.010000    -0.011167 0
      1 82 0.020000    -0.015294 0
      1 83 0.030000    -0.018420 0
      1 84 0.040000    -0.021031 0
      1 85 0.050000    -0.023310 0
      1 86 0.060000    -0.025347 0
      1 87 0.070000    -0.027203 0
      1 88 0.080000    -0.028920 0
      1 89 0.090000    -0.030520 0
      1 90 0.100000    -0.032014 0
      1 91 0.120000    -0.034705 0
      1 92 0.140000    -0.037073 0
      1 93 0.160000    -0.039182 0
      1 94 0.180000    -0.041065 0
      1 95 0.200000    -0.042737 0
      1 96 0.250000    -0.046079 0
      1 97 0.300000    -0.048369 0
      1 98 0.350000    -0.049681 0
      1 99 0.400000    -0.049954 0
      1 100 0.450000    -0.048931 0
      1 101 0.500000    -0.046834 0
      1 102 0.550000    -0.043868 0
      1 103 0.600000    -0.040210 0
      1 104 0.650000    -0.035967 0
      1 105 0.700000    -0.031242 0
      1 106 0.750000    -0.026205 0
      1 107 0.800000    -0.021023 0
      1 108 0.850000    -0.015830 0
      1 109 0.900000    -0.010633 0
      1 110 0.950000    -0.005404 0
      1 111 1.000000    0.000000  0

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