ファイルインデックス名　: File Index Name        : 1111        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N04-0016-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 63A210
翼型ファイル番号　　　　: Airfoil File No.       : 1111
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

 0.99998, 0.00021
 0.98650, 0.00223
 0.97322, 0.00423
 0.96013, 0.00620
 0.94723, 0.00815
 0.93453, 0.01007
 0.92201, 0.01196
 0.90967, 0.01381
 0.89751, 0.01564
 0.88553, 0.01742
 0.87371, 0.01917
 0.86207, 0.02088
 0.85059, 0.02256
 0.83927, 0.02422
 0.82812, 0.02585
 0.81712, 0.02744
 0.80627, 0.02896
 0.79558, 0.03044
 0.78505, 0.03184
 0.77465, 0.03319
 0.76440, 0.03451
 0.75429, 0.03578
 0.74432, 0.03702
 0.73450, 0.03824
 0.72479, 0.03941
 0.71523, 0.04055
 0.70579, 0.04166
 0.69648, 0.04273
 0.68729, 0.04377
 0.67822, 0.04478
 0.66927, 0.04574
 0.66045, 0.04668
 0.65174, 0.04759
 0.64314, 0.04845
 0.63465, 0.04929
 0.62629, 0.05009
 0.61802, 0.05087
 0.60986, 0.05161
 0.60182, 0.05232
 0.59386, 0.05299
 0.58601, 0.05365
 0.57827, 0.05427
 0.57061, 0.05487
 0.56306, 0.05544
 0.55561, 0.05598
 0.54824, 0.05650
 0.54096, 0.05699
 0.53377, 0.05746
 0.52668, 0.05791
 0.51967, 0.05834
 0.51275, 0.05874
 0.50592, 0.05912
 0.49916, 0.05947
 0.49249, 0.05980
 0.48590, 0.06012
 0.47938, 0.06041
 0.47296, 0.06068
 0.46659, 0.06093
 0.46031, 0.06116
 0.45411, 0.06138
 0.44797, 0.06156
 0.44192, 0.06174
 0.43592, 0.06189
 0.43000, 0.06203
 0.42415, 0.06215
 0.41837, 0.06225
 0.41265, 0.06234
 0.40700, 0.06240
 0.40142, 0.06245
 0.39590, 0.06249
 0.39043, 0.06251
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 0.35391, 0.06226
 0.34892, 0.06218
 0.34398, 0.06208
 0.33911, 0.06197
 0.33428, 0.06185
 0.32950, 0.06172
 0.32478, 0.06158
 0.32011, 0.06142
 0.31549, 0.06127
 0.31092, 0.06109
 0.30640, 0.06091
 0.30192, 0.06073
 0.29749, 0.06053
 0.29312, 0.06032
 0.28878, 0.06010
 0.28449, 0.05988
 0.28026, 0.05965
 0.27606, 0.05941
 0.27190, 0.05916
 0.26779, 0.05891
 0.26372, 0.05865
 0.25970, 0.05839
 0.25571, 0.05812
 0.25177, 0.05785
 0.24785, 0.05756
 0.24399, 0.05728
 0.24017, 0.05698
 0.23638, 0.05668
 0.23263, 0.05638
 0.22892, 0.05607
 0.22525, 0.05576
 0.22161, 0.05544
 0.21801, 0.05512
 0.21444, 0.05480
 0.21091, 0.05446
 0.20741, 0.05413
 0.20394, 0.05379
 0.20052, 0.05345
 0.19712, 0.05311
 0.19376, 0.05276
 0.19043, 0.05240
 0.18713, 0.05204
 0.18387, 0.05168
 0.18063, 0.05132
 0.17743, 0.05094
 0.17426, 0.05057
 0.17112, 0.05019
 0.16800, 0.04981
 0.16492, 0.04943
 0.16187, 0.04905
 0.15884, 0.04865
 0.15584, 0.04826
 0.15287, 0.04786
 0.14993, 0.04746
 0.14702, 0.04706
 0.14414, 0.04665
 0.14127, 0.04624
 0.13843, 0.04582
 0.13563, 0.04540
 0.13284, 0.04499
 0.13009, 0.04456
 0.12736, 0.04413
 0.12466, 0.04370
 0.12198, 0.04327
 0.11932, 0.04283
 0.11668, 0.04239
 0.11407, 0.04195
 0.11149, 0.04151
 0.10892, 0.04105
 0.10638, 0.04060
 0.10386, 0.04015
 0.10137, 0.03969
 0.09890, 0.03922
 0.09645, 0.03876
 0.09402, 0.03828
 0.09161, 0.03781
 0.08922, 0.03733
 0.08686, 0.03685
 0.08452, 0.03636
 0.08219, 0.03587
 0.07989, 0.03538
 0.07761, 0.03488
 0.07534, 0.03438
 0.07310, 0.03388
 0.07087, 0.03337
 0.06867, 0.03284
 0.06648, 0.03232
 0.06432, 0.03181
 0.06217, 0.03127
 0.06004, 0.03074
 0.05793, 0.03019
 0.05584, 0.02964
 0.05376, 0.02909
 0.05170, 0.02854
 0.04966, 0.02797
 0.04765, 0.02740
 0.04565, 0.02681
 0.04365, 0.02622
 0.04169, 0.02563
 0.03974, 0.02502
 0.03779, 0.02441
 0.03588, 0.02379
 0.03397, 0.02315
 0.03210, 0.02251
 0.03023, 0.02185
 0.02837, 0.02118
 0.02654, 0.02049
 0.02471, 0.01979
 0.02291, 0.01906
 0.02112, 0.01832
 0.01936, 0.01756
 0.01760, 0.01676
 0.01587, 0.01594
 0.01415, 0.01508
 0.01245, 0.01419
 0.01077, 0.01324
 0.00910, 0.01223
 0.00747, 0.01116
 0.00585, 0.01000
 0.00425, 0.00870
 0.00269, 0.00716
 0.00119, 0.00514
 0.00027, 0.00303
 0.00000, 0.00000
 0.00000, 0.00000
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 0.08806,-0.02575
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 0.10026,-0.02713
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 0.10781,-0.02792
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 0.11296,-0.02843
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