ファイルインデックス名　: File Index Name        : 1304        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N06-0026-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 12-H-12
翼型ファイル番号　　　　: Airfoil File No.       : 1304
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-A01B


座標　　　　　　　　　　: Plot Ordinates         :

 X             Y

 1.00000, 0.00000
 0.98718,-0.00131
 0.97431,-0.00192
 0.96141,-0.00193
 0.94852,-0.00142
 0.93566,-0.00047
 0.92285, 0.00084
 0.91011, 0.00245
 0.89748, 0.00427
 0.88498, 0.00618
 0.87260, 0.00823
 0.86034, 0.01042
 0.84821, 0.01270
 0.83621, 0.01505
 0.82434, 0.01747
 0.81261, 0.01994
 0.80102, 0.02244
 0.78957, 0.02495
 0.77827, 0.02747
 0.76710, 0.03000
 0.75608, 0.03251
 0.74520, 0.03501
 0.73447, 0.03748
 0.72389, 0.03991
 0.71343, 0.04233
 0.70313, 0.04470
 0.69297, 0.04703
 0.68294, 0.04931
 0.67305, 0.05155
 0.66330, 0.05374
 0.65367, 0.05588
 0.64421, 0.05795
 0.63486, 0.05996
 0.62565, 0.06191
 0.61656, 0.06381
 0.60762, 0.06565
 0.59879, 0.06743
 0.59008, 0.06917
 0.58150, 0.07084
 0.57303, 0.07246
 0.56469, 0.07401
 0.55647, 0.07551
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 0.53249, 0.07966
 0.52472, 0.08093
 0.51706, 0.08213
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 0.50206, 0.08439
 0.49472, 0.08542
 0.48749, 0.08641
 0.48036, 0.08734
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 0.46640, 0.08903
 0.45956, 0.08979
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 0.44619, 0.09115
 0.43963, 0.09176
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 0.20144, 0.08155
 0.19797, 0.08099
 0.19453, 0.08044
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 0.16526, 0.07513
 0.16218, 0.07452
 0.15913, 0.07390
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 0.14437, 0.07074
 0.14151, 0.07010
 0.13868, 0.06945
 0.13587, 0.06880
 0.13309, 0.06815
 0.13035, 0.06749
 0.12764, 0.06682
 0.12495, 0.06616
 0.12229, 0.06550
 0.11965, 0.06482
 0.11705, 0.06415
 0.11447, 0.06346
 0.11192, 0.06278
 0.10940, 0.06209
 0.10689, 0.06140
 0.10442, 0.06071
 0.10197, 0.06001
 0.09954, 0.05931
 0.09714, 0.05860
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 0.09009, 0.05644
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 0.08551, 0.05499
 0.08326, 0.05426
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 0.07882, 0.05278
 0.07663, 0.05203
 0.07446, 0.05129
 0.07232, 0.05053
 0.07020, 0.04978
 0.06810, 0.04903
 0.06602, 0.04826
 0.06397, 0.04750
 0.06193, 0.04673
 0.05992, 0.04595
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 0.05594, 0.04440
 0.05399, 0.04361
 0.05206, 0.04282
 0.05014, 0.04202
 0.04825, 0.04122
 0.04638, 0.04041
 0.04452, 0.03960
 0.04268, 0.03877
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 0.03908, 0.03710
 0.03731, 0.03626
 0.03556, 0.03540
 0.03382, 0.03453
 0.03211, 0.03367
 0.03041, 0.03278
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 0.02708, 0.03099
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 0.00884, 0.01891
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 0.00364, 0.01370
 0.00246, 0.01216
 0.00135, 0.01045
 0.00035, 0.00845
-0.00043, 0.00592
-0.00065, 0.00339
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 0.00000, 0.00000
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