ファイルインデックス名　: File Index Name        : 1108        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N04-0013-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 63-206
翼型ファイル番号　　　　: Airfoil File No.       : 1108
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-A01B1


座標　　　　　　　　　　: Plot Ordinates         :

 X             Y

 1.00000, 0.00000
 0.98661, 0.00124
 0.97341, 0.00243
 0.96042, 0.00361
 0.94761, 0.00476
 0.93499, 0.00588
 0.92256, 0.00699
 0.91031, 0.00809
 0.89823, 0.00917
 0.88632, 0.01026
 0.87458, 0.01133
 0.86301, 0.01239
 0.85161, 0.01343
 0.84036, 0.01445
 0.82928, 0.01545
 0.81834, 0.01643
 0.80756, 0.01739
 0.79693, 0.01833
 0.78646, 0.01925
 0.77611, 0.02015
 0.76591, 0.02104
 0.75585, 0.02189
 0.74593, 0.02273
 0.73615, 0.02354
 0.72650, 0.02433
 0.71697, 0.02510
 0.70758, 0.02585
 0.69831, 0.02657
 0.68916, 0.02727
 0.68013, 0.02796
 0.67122, 0.02861
 0.66243, 0.02925
 0.65375, 0.02988
 0.64519, 0.03047
 0.63673, 0.03105
 0.62839, 0.03160
 0.62016, 0.03214
 0.61202, 0.03265
 0.60400, 0.03314
 0.59607, 0.03363
 0.58824, 0.03408
 0.58053, 0.03452
 0.57289, 0.03494
 0.56536, 0.03534
 0.55792, 0.03573
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 0.54331, 0.03644
 0.53615, 0.03678
 0.52907, 0.03710
 0.52207, 0.03740
 0.51517, 0.03768
 0.50835, 0.03795
 0.50161, 0.03820
 0.49495, 0.03844
 0.48837, 0.03866
 0.48186, 0.03887
 0.47544, 0.03906
 0.46909, 0.03925
 0.46281, 0.03941
 0.45662, 0.03956
 0.45049, 0.03971
 0.44444, 0.03984
 0.43845, 0.03994
 0.43253, 0.04005
 0.42668, 0.04015
 0.42091, 0.04022
 0.41519, 0.04029
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 0.34650, 0.04025
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 0.32728, 0.03993
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 0.30887, 0.03951
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 0.29556, 0.03917
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 0.24244, 0.03745
 0.23864, 0.03725
 0.23488, 0.03702
 0.23115, 0.03679
 0.22747, 0.03656
 0.22383, 0.03631
 0.22022, 0.03606
 0.21664, 0.03581
 0.21310, 0.03555
 0.20959, 0.03529
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 0.20268, 0.03477
 0.19927, 0.03450
 0.19590, 0.03426
 0.19255, 0.03401
 0.18924, 0.03377
 0.18596, 0.03353
 0.18271, 0.03328
 0.17949, 0.03304
 0.17631, 0.03279
 0.17315, 0.03255
 0.17002, 0.03230
 0.16692, 0.03206
 0.16386, 0.03181
 0.16082, 0.03156
 0.15780, 0.03131
 0.15481, 0.03106
 0.15185, 0.03080
 0.14892, 0.03054
 0.14602, 0.03028
 0.14315, 0.03000
 0.14029, 0.02973
 0.13747, 0.02946
 0.13467, 0.02919
 0.13190, 0.02890
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 0.12643, 0.02834
 0.12373, 0.02806
 0.12106, 0.02777
 0.11840, 0.02748
 0.11577, 0.02719
 0.11317, 0.02690
 0.11058, 0.02660
 0.10803, 0.02631
 0.10549, 0.02601
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 0.10050, 0.02541
 0.09802, 0.02510
 0.09558, 0.02480
 0.09314, 0.02449
 0.09074, 0.02418
 0.08836, 0.02385
 0.08599, 0.02354
 0.08365, 0.02323
 0.08133, 0.02290
 0.07902, 0.02258
 0.07674, 0.02225
 0.07448, 0.02192
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 0.07001, 0.02124
 0.06780, 0.02091
 0.06561, 0.02056
 0.06344, 0.02021
 0.06129, 0.01985
 0.05916, 0.01949
 0.05705, 0.01913
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 0.05287, 0.01840
 0.05081, 0.01804
 0.04877, 0.01765
 0.04674, 0.01728
 0.04472, 0.01689
 0.04274, 0.01650
 0.04076, 0.01610
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 0.03686, 0.01530
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 0.00141, 0.00317
 0.00041, 0.00183
 0.00000, 0.00000
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