ファイルインデックス名　: File Index Name        : 1141        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N04-0046-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 64-210
翼型ファイル番号　　　　: Airfoil File No.       : 1141
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
 0.98659, 0.00145
 0.97337, 0.00293
 0.96035, 0.00443
 0.94751, 0.00596
 0.93486, 0.00749
 0.92239, 0.00905
 0.91010, 0.01061
 0.89798, 0.01217
 0.88603, 0.01374
 0.87425, 0.01529
 0.86264, 0.01684
 0.85119, 0.01837
 0.83991, 0.01989
 0.82878, 0.02138
 0.81781, 0.02284
 0.80698, 0.02430
 0.79631, 0.02572
 0.78580, 0.02712
 0.77541, 0.02850
 0.76518, 0.02984
 0.75508, 0.03115
 0.74512, 0.03244
 0.73530, 0.03368
 0.72561, 0.03490
 0.71605, 0.03608
 0.70662, 0.03724
 0.69732, 0.03836
 0.68814, 0.03944
 0.67908, 0.04051
 0.67013, 0.04154
 0.66132, 0.04253
 0.65261, 0.04350
 0.64402, 0.04444
 0.63553, 0.04534
 0.62717, 0.04622
 0.61891, 0.04706
 0.61075, 0.04788
 0.60270, 0.04868
 0.59475, 0.04943
 0.58690, 0.05017
 0.57916, 0.05087
 0.57150, 0.05154
 0.56395, 0.05219
 0.55649, 0.05282
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 0.54184, 0.05398
 0.53466, 0.05453
 0.52757, 0.05505
 0.52055, 0.05555
 0.51363, 0.05602
 0.50680, 0.05647
 0.50004, 0.05688
 0.49337, 0.05728
 0.48677, 0.05766
 0.48026, 0.05801
 0.47383, 0.05834
 0.46746, 0.05864
 0.46118, 0.05892
 0.45498, 0.05918
 0.44884, 0.05942
 0.44278, 0.05964
 0.43678, 0.05984
 0.43086, 0.06001
 0.42500, 0.06016
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 0.41350, 0.06041
 0.40786, 0.06049
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 0.37528, 0.06054
 0.37007, 0.06048
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 0.34978, 0.06011
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 0.33514, 0.05973
 0.33036, 0.05959
 0.32565, 0.05943
 0.32097, 0.05927
 0.31635, 0.05909
 0.31178, 0.05891
 0.30726, 0.05871
 0.30278, 0.05852
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 0.29398, 0.05810
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 0.28111, 0.05741
 0.27691, 0.05716
 0.27275, 0.05691
 0.26863, 0.05666
 0.26456, 0.05639
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 0.25655, 0.05586
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 0.24868, 0.05529
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 0.23720, 0.05441
 0.23344, 0.05411
 0.22973, 0.05380
 0.22606, 0.05349
 0.22241, 0.05318
 0.21881, 0.05285
 0.21524, 0.05253
 0.21170, 0.05221
 0.20820, 0.05187
 0.20473, 0.05154
 0.20130, 0.05120
 0.19790, 0.05085
 0.19454, 0.05051
 0.19120, 0.05016
 0.18790, 0.04981
 0.18463, 0.04945
 0.18139, 0.04910
 0.17818, 0.04874
 0.17501, 0.04838
 0.17186, 0.04801
 0.16874, 0.04764
 0.16565, 0.04727
 0.16259, 0.04690
 0.15956, 0.04652
 0.15656, 0.04614
 0.15358, 0.04576
 0.15063, 0.04537
 0.14771, 0.04497
 0.14483, 0.04459
 0.14196, 0.04419
 0.13911, 0.04378
 0.13631, 0.04339
 0.13351, 0.04298
 0.13076, 0.04257
 0.12802, 0.04216
 0.12530, 0.04175
 0.12262, 0.04133
 0.11995, 0.04092
 0.11731, 0.04049
 0.11470, 0.04007
 0.11210, 0.03964
 0.10953, 0.03922
 0.10698, 0.03878
 0.10446, 0.03835
 0.10196, 0.03791
 0.09949, 0.03747
 0.09702, 0.03703
 0.09459, 0.03658
 0.09217, 0.03613
 0.08978, 0.03568
 0.08740, 0.03523
 0.08505, 0.03477
 0.08272, 0.03431
 0.08041, 0.03384
 0.07812, 0.03337
 0.07585, 0.03290
 0.07360, 0.03242
 0.07136, 0.03194
 0.06915, 0.03145
 0.06695, 0.03097
 0.06478, 0.03047
 0.06263, 0.02997
 0.06049, 0.02947
 0.05837, 0.02896
 0.05627, 0.02844
 0.05418, 0.02792
 0.05211, 0.02740
 0.05007, 0.02686
 0.04804, 0.02633
 0.04603, 0.02578
 0.04403, 0.02523
 0.04205, 0.02467
 0.04009, 0.02411
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 0.03622, 0.02294
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 0.00596, 0.01000
 0.00435, 0.00870
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 0.00125, 0.00512
 0.00031, 0.00300
 0.00000, 0.00000
 0.00000, 0.00000
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 1.00000, 0.00000