Learning Forum

[Ryan Hirani]

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]

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