ファイルインデックス名　: File Index Name        : 1138        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N04-0043-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 64-206
翼型ファイル番号　　　　: Airfoil File No.       : 1138
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
 0.98660, 0.00128
 0.97341, 0.00253
 0.96040, 0.00376
 0.94759, 0.00496
 0.93497, 0.00615
 0.92253, 0.00731
 0.91028, 0.00845
 0.89819, 0.00958
 0.88629, 0.01071
 0.87455, 0.01182
 0.86297, 0.01290
 0.85156, 0.01398
 0.84032, 0.01502
 0.82923, 0.01604
 0.81829, 0.01704
 0.80751, 0.01802
 0.79688, 0.01899
 0.78640, 0.01992
 0.77606, 0.02083
 0.76586, 0.02173
 0.75580, 0.02260
 0.74588, 0.02344
 0.73610, 0.02425
 0.72644, 0.02505
 0.71692, 0.02581
 0.70752, 0.02655
 0.69825, 0.02727
 0.68910, 0.02797
 0.68008, 0.02865
 0.67116, 0.02931
 0.66238, 0.02994
 0.65370, 0.03055
 0.64514, 0.03115
 0.63668, 0.03172
 0.62834, 0.03227
 0.62011, 0.03279
 0.61198, 0.03330
 0.60395, 0.03379
 0.59602, 0.03427
 0.58820, 0.03471
 0.58048, 0.03514
 0.57285, 0.03556
 0.56531, 0.03595
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 0.54327, 0.03702
 0.53611, 0.03735
 0.52903, 0.03766
 0.52204, 0.03794
 0.51513, 0.03822
 0.50831, 0.03848
 0.50157, 0.03873
 0.49491, 0.03895
 0.48833, 0.03917
 0.48183, 0.03936
 0.47541, 0.03955
 0.46906, 0.03971
 0.46278, 0.03987
 0.45659, 0.04001
 0.45046, 0.04012
 0.44441, 0.04024
 0.43842, 0.04035
 0.43251, 0.04043
 0.42666, 0.04050
 0.42089, 0.04055
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 0.38224, 0.04057
 0.37697, 0.04053
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 0.32263, 0.03950
 0.31802, 0.03937
 0.31344, 0.03923
 0.30891, 0.03909
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 0.29562, 0.03865
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 0.23874, 0.03610
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 0.23126, 0.03568
 0.22757, 0.03547
 0.22392, 0.03525
 0.22031, 0.03504
 0.21673, 0.03481
 0.21319, 0.03459
 0.20968, 0.03436
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 0.19598, 0.03343
 0.19262, 0.03320
 0.18932, 0.03295
 0.18604, 0.03271
 0.18279, 0.03247
 0.17957, 0.03223
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 0.17323, 0.03172
 0.17010, 0.03148
 0.16700, 0.03122
 0.16393, 0.03097
 0.16089, 0.03072
 0.15788, 0.03045
 0.15489, 0.03019
 0.15193, 0.02993
 0.14900, 0.02966
 0.14610, 0.02940
 0.14323, 0.02913
 0.14037, 0.02886
 0.13755, 0.02859
 0.13475, 0.02831
 0.13198, 0.02804
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 0.12651, 0.02748
 0.12381, 0.02720
 0.12113, 0.02692
 0.11848, 0.02663
 0.11585, 0.02634
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 0.10557, 0.02518
 0.10305, 0.02488
 0.10057, 0.02459
 0.09809, 0.02429
 0.09565, 0.02399
 0.09322, 0.02368
 0.09081, 0.02338
 0.08843, 0.02307
 0.08606, 0.02276
 0.08372, 0.02245
 0.08140, 0.02214
 0.07909, 0.02182
 0.07681, 0.02150
 0.07455, 0.02118
 0.07229, 0.02086
 0.07007, 0.02053
 0.06786, 0.02020
 0.06568, 0.01987
 0.06351, 0.01954
 0.06135, 0.01919
 0.05922, 0.01885
 0.05710, 0.01851
 0.05500, 0.01817
 0.05292, 0.01781
 0.05086, 0.01746
 0.04882, 0.01710
 0.04679, 0.01673
 0.04477, 0.01636
 0.04278, 0.01599
 0.04081, 0.01562
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 0.03690, 0.01485
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 0.00141, 0.00315
 0.00041, 0.00183
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