ファイルインデックス名　: File Index Name        : 1116        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N04-0021-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 63>>1<<-412
翼型ファイル番号　　　　: Airfoil File No.       : 1116
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
 0.98650, 0.00243
 0.97322, 0.00479
 0.96012, 0.00709
 0.94722, 0.00933
 0.93452, 0.01152
 0.92200, 0.01368
 0.90966, 0.01581
 0.89749, 0.01791
 0.88550, 0.02003
 0.87367, 0.02211
 0.86202, 0.02418
 0.85053, 0.02621
 0.83920, 0.02821
 0.82803, 0.03017
 0.81702, 0.03211
 0.80616, 0.03400
 0.79545, 0.03585
 0.78490, 0.03767
 0.77448, 0.03945
 0.76421, 0.04121
 0.75408, 0.04291
 0.74409, 0.04457
 0.73424, 0.04619
 0.72452, 0.04777
 0.71493, 0.04931
 0.70547, 0.05081
 0.69614, 0.05226
 0.68693, 0.05368
 0.67784, 0.05505
 0.66887, 0.05638
 0.66003, 0.05766
 0.65130, 0.05891
 0.64269, 0.06011
 0.63418, 0.06128
 0.62579, 0.06240
 0.61751, 0.06349
 0.60933, 0.06453
 0.60127, 0.06554
 0.59330, 0.06650
 0.58543, 0.06742
 0.57767, 0.06831
 0.57000, 0.06917
 0.56243, 0.06999
 0.55497, 0.07077
 0.54758, 0.07152
 0.54029, 0.07224
 0.53309, 0.07293
 0.52599, 0.07359
 0.51897, 0.07421
 0.51204, 0.07480
 0.50519, 0.07535
 0.49843, 0.07588
 0.49174, 0.07638
 0.48514, 0.07684
 0.47862, 0.07729
 0.47218, 0.07770
 0.46581, 0.07807
 0.45952, 0.07843
 0.45331, 0.07875
 0.44717, 0.07906
 0.44110, 0.07934
 0.43510, 0.07958
 0.42917, 0.07982
 0.42332, 0.08001
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 0.22443, 0.07258
 0.22080, 0.07216
 0.21720, 0.07175
 0.21364, 0.07133
 0.21012, 0.07089
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 0.19635, 0.06912
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 0.18311, 0.06725
 0.17988, 0.06677
 0.17668, 0.06629
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 0.16116, 0.06380
 0.15814, 0.06329
 0.15514, 0.06277
 0.15218, 0.06225
 0.14924, 0.06172
 0.14634, 0.06119
 0.14346, 0.06066
 0.14061, 0.06012
 0.13777, 0.05958
 0.13498, 0.05903
 0.13219, 0.05847
 0.12945, 0.05792
 0.12673, 0.05736
 0.12403, 0.05680
 0.12135, 0.05623
 0.11870, 0.05566
 0.11607, 0.05508
 0.11347, 0.05450
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 0.10580, 0.05272
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 0.09834, 0.05092
 0.09589, 0.05030
 0.09348, 0.04969
 0.09107, 0.04907
 0.08869, 0.04844
 0.08633, 0.04781
 0.08400, 0.04718
 0.08168, 0.04653
 0.07939, 0.04589
 0.07711, 0.04524
 0.07486, 0.04458
 0.07262, 0.04392
 0.07040, 0.04325
 0.06821, 0.04258
 0.06602, 0.04189
 0.06387, 0.04121
 0.06173, 0.04051
 0.05961, 0.03980
 0.05751, 0.03910
 0.05542, 0.03839
 0.05335, 0.03766
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 0.04928, 0.03618
 0.04727, 0.03544
 0.04527, 0.03468
 0.04329, 0.03391
 0.04133, 0.03313
 0.03939, 0.03235
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 0.03556, 0.03074
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 0.00568, 0.01321
 0.00410, 0.01159
 0.00256, 0.00964
 0.00109, 0.00704
 0.00020, 0.00421
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 0.00000, 0.00000
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 1.00000, 0.00000