ファイルインデックス名　: File Index Name        : 1171        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N04-0076-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 65>>1<<-212
翼型ファイル番号　　　　: Airfoil File No.       : 1171
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
 0.98657, 0.00166
 0.97333, 0.00340
 0.96028, 0.00524
 0.94741, 0.00713
 0.93473, 0.00908
 0.92222, 0.01105
 0.90989, 0.01306
 0.89773, 0.01506
 0.88575, 0.01705
 0.87394, 0.01904
 0.86229, 0.02101
 0.85081, 0.02296
 0.83949, 0.02487
 0.82833, 0.02675
 0.81732, 0.02859
 0.80647, 0.03041
 0.79577, 0.03219
 0.78522, 0.03393
 0.77481, 0.03563
 0.76455, 0.03730
 0.75442, 0.03892
 0.74444, 0.04050
 0.73460, 0.04203
 0.72489, 0.04351
 0.71530, 0.04496
 0.70586, 0.04636
 0.69653, 0.04773
 0.68733, 0.04906
 0.67825, 0.05034
 0.66929, 0.05158
 0.66046, 0.05278
 0.65173, 0.05394
 0.64312, 0.05505
 0.63462, 0.05612
 0.62625, 0.05714
 0.61798, 0.05813
 0.60981, 0.05908
 0.60175, 0.05998
 0.59379, 0.06085
 0.58593, 0.06168
 0.57818, 0.06247
 0.57052, 0.06322
 0.56296, 0.06394
 0.55550, 0.06460
 0.54813, 0.06525
 0.54085, 0.06584
 0.53366, 0.06640
 0.52657, 0.06692
 0.51955, 0.06741
 0.51264, 0.06786
 0.50580, 0.06828
 0.49905, 0.06865
 0.49238, 0.06898
 0.48580, 0.06929
 0.47928, 0.06956
 0.47286, 0.06980
 0.46651, 0.07001
 0.46023, 0.07019
 0.45404, 0.07035
 0.44791, 0.07048
 0.44186, 0.07058
 0.43587, 0.07067
 0.42996, 0.07072
 0.42411, 0.07076
 0.41834, 0.07077
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 0.38506, 0.07046
 0.37974, 0.07035
 0.37447, 0.07022
 0.36926, 0.07009
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 0.34407, 0.06921
 0.33920, 0.06900
 0.33438, 0.06880
 0.32961, 0.06856
 0.32490, 0.06834
 0.32023, 0.06810
 0.31562, 0.06785
 0.31105, 0.06758
 0.30653, 0.06732
 0.30206, 0.06705
 0.29764, 0.06677
 0.29327, 0.06648
 0.28894, 0.06618
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 0.28042, 0.06558
 0.27622, 0.06526
 0.27207, 0.06494
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 0.26390, 0.06429
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 0.24418, 0.06255
 0.24036, 0.06218
 0.23657, 0.06183
 0.23283, 0.06145
 0.22912, 0.06108
 0.22545, 0.06070
 0.22181, 0.06031
 0.21821, 0.05992
 0.21465, 0.05953
 0.21112, 0.05913
 0.20762, 0.05874
 0.20416, 0.05833
 0.20073, 0.05792
 0.19734, 0.05751
 0.19398, 0.05710
 0.19065, 0.05667
 0.18735, 0.05626
 0.18409, 0.05583
 0.18086, 0.05540
 0.17765, 0.05497
 0.17449, 0.05453
 0.17135, 0.05410
 0.16823, 0.05365
 0.16515, 0.05321
 0.16210, 0.05276
 0.15907, 0.05232
 0.15607, 0.05186
 0.15310, 0.05141
 0.15016, 0.05095
 0.14725, 0.05048
 0.14437, 0.05002
 0.14151, 0.04956
 0.13867, 0.04909
 0.13587, 0.04861
 0.13308, 0.04813
 0.13033, 0.04766
 0.12760, 0.04718
 0.12489, 0.04670
 0.12221, 0.04622
 0.11955, 0.04572
 0.11691, 0.04523
 0.11430, 0.04474
 0.11172, 0.04424
 0.10915, 0.04373
 0.10661, 0.04324
 0.10409, 0.04272
 0.10160, 0.04221
 0.09913, 0.04170
 0.09667, 0.04118
 0.09425, 0.04066
 0.09183, 0.04013
 0.08944, 0.03961
 0.08708, 0.03908
 0.08473, 0.03854
 0.08241, 0.03801
 0.08010, 0.03747
 0.07782, 0.03693
 0.07556, 0.03638
 0.07331, 0.03583
 0.07108, 0.03528
 0.06888, 0.03472
 0.06668, 0.03415
 0.06452, 0.03359
 0.06237, 0.03302
 0.06024, 0.03245
 0.05813, 0.03187
 0.05603, 0.03129
 0.05394, 0.03070
 0.05188, 0.03011
 0.04985, 0.02950
 0.04783, 0.02890
 0.04582, 0.02828
 0.04382, 0.02766
 0.04185, 0.02703
 0.03990, 0.02639
 0.03795, 0.02574
 0.03604, 0.02509
 0.03412, 0.02443
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 0.03037, 0.02308
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 0.02484, 0.02096
 0.02303, 0.02023
 0.02123, 0.01950
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 0.01594, 0.01717
 0.01422, 0.01633
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 0.00749, 0.01238
 0.00586, 0.01115
 0.00426, 0.00973
 0.00269, 0.00802
 0.00120, 0.00575
 0.00028, 0.00337
 0.00000, 0.00000
 0.00000, 0.00000
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 0.08334,-0.02860
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 0.11302,-0.03285
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 1.00000, 0.00000