ファイルインデックス名　: File Index Name        : 1223        .A00
翼型整理番号　　　　　　: Airfoil Serial No.     : N01-0073-0
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 2212
翼型ファイル番号　　　　: Airfoil File No.       : 1223
翼型情報　　　　　　　　: Airfoil Information    : Computed

算出前縁半径　　　　　　: Computed L.E.R.        : 1.59 %
算出前縁傾斜　　　　　　: Computed Slope of L.E. : 0.2
算出プログラム番号　　　: Computed Program No.   : ウハク-40B


座標　　　　　　　　　　: Plot Ordinates         :

 X             Y

 1.00006, 0.00126
 0.98686, 0.00376
 0.97386, 0.00619
 0.96104, 0.00855
 0.94840, 0.01083
 0.93595, 0.01305
 0.92367, 0.01520
 0.91157, 0.01729
 0.89964, 0.01932
 0.88788, 0.02129
 0.87628, 0.02320
 0.86484, 0.02506
 0.85356, 0.02687
 0.84244, 0.02863
 0.83148, 0.03034
 0.82066, 0.03200
 0.80999, 0.03362
 0.79947, 0.03519
 0.78909, 0.03672
 0.77885, 0.03820
 0.76874, 0.03965
 0.75878, 0.04106
 0.74894, 0.04243
 0.73924, 0.04376
 0.72967, 0.04506
 0.72022, 0.04632
 0.71089, 0.04754
 0.70169, 0.04874
 0.69261, 0.04990
 0.68364, 0.05103
 0.67479, 0.05213
 0.66606, 0.05320
 0.65743, 0.05423
 0.64892, 0.05524
 0.64052, 0.05623
 0.63222, 0.05718
 0.62402, 0.05811
 0.61593, 0.05901
 0.60794, 0.05989
 0.60005, 0.06074
 0.59226, 0.06156
 0.58456, 0.06236
 0.57696, 0.06314
 0.56945, 0.06390
 0.56203, 0.06463
 0.55471, 0.06534
 0.54747, 0.06603
 0.54032, 0.06669
 0.53326, 0.06734
 0.52628, 0.06796
 0.51938, 0.06857
 0.51257, 0.06915
 0.50583, 0.06972
 0.49918, 0.07027
 0.49260, 0.07079
 0.48610, 0.07130
 0.47968, 0.07180
 0.47333, 0.07227
 0.46706, 0.07273
 0.46085, 0.07317
 0.45472, 0.07359
 0.44866, 0.07399
 0.44267, 0.07438
 0.43675, 0.07476
 0.43089, 0.07512
 0.42510, 0.07546
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 0.38634, 0.07745
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 0.35045, 0.07878
 0.34555, 0.07892
 0.34069, 0.07905
 0.33589, 0.07917
 0.33114, 0.07928
 0.32643, 0.07937
 0.32178, 0.07945
 0.31718, 0.07953
 0.31262, 0.07959
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 0.24577, 0.07923
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 0.23814, 0.07902
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 0.23067, 0.07878
 0.22699, 0.07865
 0.22334, 0.07851
 0.21973, 0.07836
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 0.21261, 0.07804
 0.20911, 0.07787
 0.20563, 0.07769
 0.20219, 0.07750
 0.19872, 0.07730
 0.19516, 0.07709
 0.19164, 0.07686
 0.18816, 0.07661
 0.18471, 0.07635
 0.18129, 0.07607
 0.17791, 0.07577
 0.17455, 0.07545
 0.17124, 0.07512
 0.16795, 0.07477
 0.16470, 0.07441
 0.16148, 0.07403
 0.15829, 0.07363
 0.15513, 0.07322
 0.15200, 0.07280
 0.14891, 0.07236
 0.14584, 0.07191
 0.14280, 0.07145
 0.13979, 0.07097
 0.13682, 0.07048
 0.13387, 0.06997
 0.13095, 0.06946
 0.12806, 0.06893
 0.12519, 0.06838
 0.12236, 0.06783
 0.11955, 0.06726
 0.11677, 0.06668
 0.11402, 0.06609
 0.11129, 0.06549
 0.10859, 0.06487
 0.10592, 0.06425
 0.10327, 0.06361
 0.10065, 0.06296
 0.09806, 0.06230
 0.09549, 0.06163
 0.09294, 0.06095
 0.09042, 0.06026
 0.08793, 0.05956
 0.08545, 0.05884
 0.08301, 0.05812
 0.08059, 0.05738
 0.07819, 0.05663
 0.07581, 0.05587
 0.07346, 0.05510
 0.07114, 0.05432
 0.06883, 0.05353
 0.06655, 0.05273
 0.06429, 0.05191
 0.06206, 0.05108
 0.05984, 0.05025
 0.05765, 0.04940
 0.05549, 0.04853
 0.05334, 0.04766
 0.05122, 0.04677
 0.04912, 0.04587
 0.04704, 0.04495
 0.04498, 0.04402
 0.04294, 0.04307
 0.04093, 0.04211
 0.03894, 0.04114
 0.03697, 0.04015
 0.03502, 0.03914
 0.03310, 0.03811
 0.03119, 0.03706
 0.02931, 0.03599
 0.02745, 0.03490
 0.02561, 0.03378
 0.02380, 0.03264
 0.02201, 0.03147
 0.02024, 0.03027
 0.01850, 0.02903
 0.01678, 0.02776
 0.01508, 0.02644
 0.01342, 0.02508
 0.01178, 0.02366
 0.01017, 0.02218
 0.00860, 0.02061
 0.00706, 0.01896
 0.00556, 0.01718
 0.00411, 0.01524
 0.00272, 0.01308
 0.00143, 0.01057
 0.00028, 0.00737
-0.00026, 0.00420
 0.00000, 0.00000
 0.00000, 0.00000
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