ファイルインデックス名　: File Index Name        : 1169        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N04-0074-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 65-209
翼型ファイル番号　　　　: Airfoil File No.       : 1169
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

 1.00000, 0.00000
 0.98658, 0.00152
 0.97336, 0.00308
 0.96033, 0.00468
 0.94748, 0.00630
 0.93482, 0.00794
 0.92234, 0.00958
 0.91004, 0.01123
 0.89792, 0.01287
 0.88597, 0.01448
 0.87419, 0.01609
 0.86257, 0.01767
 0.85112, 0.01923
 0.83983, 0.02075
 0.82871, 0.02225
 0.81773, 0.02372
 0.80691, 0.02515
 0.79624, 0.02655
 0.78573, 0.02791
 0.77535, 0.02924
 0.76512, 0.03054
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 0.74507, 0.03303
 0.73526, 0.03422
 0.72557, 0.03537
 0.71602, 0.03649
 0.70660, 0.03758
 0.69730, 0.03863
 0.68812, 0.03964
 0.67907, 0.04062
 0.67013, 0.04156
 0.66132, 0.04247
 0.65262, 0.04336
 0.64404, 0.04420
 0.63556, 0.04501
 0.62721, 0.04578
 0.61895, 0.04653
 0.61080, 0.04724
 0.60276, 0.04793
 0.59482, 0.04859
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 0.52073, 0.05347
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 0.50699, 0.05411
 0.50025, 0.05438
 0.49359, 0.05462
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 0.47409, 0.05520
 0.46774, 0.05534
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 0.44915, 0.05565
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 0.23769, 0.04857
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 0.16002, 0.04104
 0.15702, 0.04068
 0.15403, 0.04032
 0.15109, 0.03996
 0.14817, 0.03959
 0.14528, 0.03923
 0.14241, 0.03885
 0.13956, 0.03848
 0.13675, 0.03812
 0.13395, 0.03773
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 0.11774, 0.03543
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 0.09989, 0.03265
 0.09742, 0.03225
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 0.09256, 0.03142
 0.09017, 0.03100
 0.08779, 0.03059
 0.08544, 0.03017
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 0.07397, 0.02803
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 0.06951, 0.02716
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 0.06514, 0.02628
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