ファイルインデックス名　: File Index Name        : 1142        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N04-0047-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 64A210
翼型ファイル番号　　　　: Airfoil File No.       : 1142
翼型情報　　　　　　　　: Airfoil Information    : Original

算出前縁半径　　　　　　: Computed L.E.R.        : ?
算出前縁傾斜　　　　　　: Computed Slope of L.E. : ?
算出プログラム番号　　　: Computed Program No.   : VB6B05-A01C


座標　　　　　　　　　　: Plot Ordinates         :

 X             Y

 0.99998, 0.00021
 0.98649, 0.00227
 0.97321, 0.00432
 0.96012, 0.00634
 0.94722, 0.00832
 0.93451, 0.01028
 0.92199, 0.01221
 0.90965, 0.01411
 0.89748, 0.01598
 0.88549, 0.01779
 0.87367, 0.01958
 0.86203, 0.02133
 0.85054, 0.02304
 0.83922, 0.02474
 0.82806, 0.02640
 0.81706, 0.02802
 0.80621, 0.02959
 0.79552, 0.03109
 0.78498, 0.03253
 0.77458, 0.03392
 0.76433, 0.03526
 0.75422, 0.03656
 0.74425, 0.03783
 0.73442, 0.03905
 0.72472, 0.04024
 0.71515, 0.04139
 0.70571, 0.04251
 0.69640, 0.04358
 0.68721, 0.04461
 0.67814, 0.04561
 0.66919, 0.04657
 0.66037, 0.04750
 0.65166, 0.04840
 0.64307, 0.04925
 0.63458, 0.05009
 0.62621, 0.05089
 0.61795, 0.05165
 0.60979, 0.05239
 0.60174, 0.05310
 0.59379, 0.05378
 0.58593, 0.05444
 0.57819, 0.05506
 0.57054, 0.05565
 0.56298, 0.05622
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 0.54816, 0.05728
 0.54089, 0.05776
 0.53370, 0.05823
 0.52661, 0.05867
 0.51960, 0.05908
 0.51268, 0.05947
 0.50585, 0.05984
 0.49910, 0.06018
 0.49242, 0.06051
 0.48584, 0.06080
 0.47932, 0.06108
 0.47290, 0.06133
 0.46653, 0.06156
 0.46025, 0.06177
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 0.32016, 0.06086
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 0.23274, 0.05523
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 0.22536, 0.05459
 0.22172, 0.05425
 0.21812, 0.05392
 0.21455, 0.05358
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 0.19389, 0.05147
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 0.18399, 0.05037
 0.18076, 0.04999
 0.17755, 0.04962
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 0.17124, 0.04886
 0.16813, 0.04847
 0.16505, 0.04809
 0.16200, 0.04769
 0.15897, 0.04730
 0.15597, 0.04690
 0.15300, 0.04651
 0.15006, 0.04610
 0.14715, 0.04570
 0.14426, 0.04529
 0.14140, 0.04489
 0.13856, 0.04448
 0.13576, 0.04406
 0.13297, 0.04364
 0.13022, 0.04322
 0.12749, 0.04280
 0.12478, 0.04238
 0.12210, 0.04195
 0.11944, 0.04152
 0.11680, 0.04109
 0.11420, 0.04066
 0.11161, 0.04022
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 0.10650, 0.03933
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 0.09902, 0.03799
 0.09656, 0.03752
 0.09414, 0.03706
 0.09172, 0.03660
 0.08934, 0.03613
 0.08697, 0.03566
 0.08463, 0.03519
 0.08230, 0.03472
 0.08000, 0.03424
 0.07771, 0.03375
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 0.07321, 0.03277
 0.07097, 0.03228
 0.06877, 0.03179
 0.06658, 0.03129
 0.06442, 0.03078
 0.06227, 0.03028
 0.06013, 0.02976
 0.05802, 0.02925
 0.05592, 0.02872
 0.05384, 0.02820
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 0.04372, 0.02546
 0.04176, 0.02489
 0.03980, 0.02431
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 0.00586, 0.00987
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 0.00270, 0.00705
 0.00120, 0.00504
 0.00028, 0.00295
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