ファイルインデックス名　: File Index Name        : 1135        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N04-0040-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 64-108
翼型ファイル番号　　　　: Airfoil File No.       : 1135
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
 0.98667, 0.00087
 0.97354, 0.00181
 0.96060, 0.00280
 0.94785, 0.00382
 0.93528, 0.00489
 0.92290, 0.00598
 0.91069, 0.00709
 0.89865, 0.00821
 0.88680, 0.00935
 0.87510, 0.01048
 0.86357, 0.01162
 0.85220, 0.01277
 0.84100, 0.01389
 0.82995, 0.01500
 0.81905, 0.01611
 0.80831, 0.01720
 0.79771, 0.01826
 0.78727, 0.01932
 0.77695, 0.02035
 0.76679, 0.02138
 0.75676, 0.02237
 0.74687, 0.02334
 0.73712, 0.02428
 0.72749, 0.02521
 0.71799, 0.02611
 0.70863, 0.02699
 0.69938, 0.02784
 0.69026, 0.02867
 0.68125, 0.02948
 0.67236, 0.03027
 0.66360, 0.03104
 0.65493, 0.03178
 0.64639, 0.03250
 0.63795, 0.03321
 0.62964, 0.03388
 0.62142, 0.03453
 0.61330, 0.03516
 0.60530, 0.03578
 0.59738, 0.03637
 0.58957, 0.03694
 0.58186, 0.03749
 0.57424, 0.03802
 0.56672, 0.03852
 0.55930, 0.03900
 0.55196, 0.03947
 0.54471, 0.03992
 0.53755, 0.04035
 0.53049, 0.04076
 0.52350, 0.04115
 0.51661, 0.04152
 0.50979, 0.04187
 0.50306, 0.04221
 0.49640, 0.04253
 0.48983, 0.04283
 0.48333, 0.04310
 0.47692, 0.04337
 0.47057, 0.04362
 0.46430, 0.04385
 0.45811, 0.04406
 0.45198, 0.04425
 0.44593, 0.04443
 0.43995, 0.04459
 0.43403, 0.04474
 0.42818, 0.04487
 0.42241, 0.04499
 0.41670, 0.04508
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 0.40547, 0.04523
 0.39995, 0.04528
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 0.38376, 0.04530
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 0.37326, 0.04524
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 0.34801, 0.04491
 0.34313, 0.04483
 0.33829, 0.04474
 0.33350, 0.04463
 0.32878, 0.04453
 0.32409, 0.04442
 0.31947, 0.04430
 0.31488, 0.04417
 0.31035, 0.04404
 0.30586, 0.04390
 0.30142, 0.04376
 0.29704, 0.04360
 0.29268, 0.04345
 0.28838, 0.04329
 0.28413, 0.04312
 0.27991, 0.04295
 0.27574, 0.04278
 0.27161, 0.04259
 0.26753, 0.04241
 0.26349, 0.04221
 0.25948, 0.04202
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 0.25159, 0.04162
 0.24771, 0.04142
 0.24387, 0.04121
 0.24006, 0.04099
 0.23629, 0.04077
 0.23256, 0.04055
 0.22887, 0.04033
 0.22520, 0.04010
 0.22158, 0.03987
 0.21799, 0.03964
 0.21444, 0.03940
 0.21092, 0.03916
 0.20743, 0.03892
 0.20398, 0.03867
 0.20057, 0.03842
 0.19719, 0.03817
 0.19383, 0.03791
 0.19051, 0.03765
 0.18722, 0.03740
 0.18396, 0.03714
 0.18073, 0.03687
 0.17754, 0.03661
 0.17437, 0.03634
 0.17123, 0.03606
 0.16813, 0.03579
 0.16505, 0.03551
 0.16200, 0.03524
 0.15897, 0.03496
 0.15597, 0.03467
 0.15300, 0.03439
 0.15007, 0.03409
 0.14716, 0.03381
 0.14427, 0.03352
 0.14140, 0.03322
 0.13858, 0.03293
 0.13576, 0.03263
 0.13298, 0.03233
 0.13022, 0.03203
 0.12749, 0.03172
 0.12478, 0.03142
 0.12209, 0.03112
 0.11943, 0.03080
 0.11679, 0.03049
 0.11417, 0.03017
 0.11158, 0.02985
 0.10901, 0.02954
 0.10646, 0.02922
 0.10394, 0.02889
 0.10144, 0.02857
 0.09895, 0.02824
 0.09650, 0.02791
 0.09405, 0.02758
 0.09164, 0.02724
 0.08924, 0.02690
 0.08686, 0.02656
 0.08451, 0.02622
 0.08217, 0.02588
 0.07986, 0.02553
 0.07756, 0.02518
 0.07529, 0.02483
 0.07302, 0.02447
 0.07079, 0.02411
 0.06856, 0.02374
 0.06637, 0.02338
 0.06418, 0.02301
 0.06202, 0.02263
 0.05988, 0.02225
 0.05774, 0.02187
 0.05563, 0.02148
 0.05353, 0.02109
 0.05146, 0.02069
 0.04941, 0.02029
 0.04736, 0.01988
 0.04533, 0.01947
 0.04333, 0.01905
 0.04134, 0.01862
 0.03936, 0.01819
 0.03740, 0.01776
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 0.01687, 0.01229
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 0.00479, 0.00687
 0.00313, 0.00565
 0.00151, 0.00405
 0.00046, 0.00237
 0.00000, 0.00000
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