ファイルインデックス名　: File Index Name        : 1309        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N06-0031-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 9-H-12
翼型ファイル番号　　　　: Airfoil File No.       : 1309
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
 0.98699,-0.00070
 0.97396,-0.00085
 0.96093,-0.00052
 0.94792, 0.00023
 0.93497, 0.00131
 0.92209, 0.00267
 0.90930, 0.00427
 0.89662, 0.00600
 0.88410, 0.00779
 0.87169, 0.00969
 0.85942, 0.01167
 0.84729, 0.01373
 0.83530, 0.01582
 0.82344, 0.01797
 0.81173, 0.02014
 0.80016, 0.02234
 0.78873, 0.02456
 0.77744, 0.02679
 0.76628, 0.02903
 0.75527, 0.03127
 0.74439, 0.03351
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 0.72307, 0.03795
 0.71260, 0.04016
 0.70228, 0.04233
 0.69210, 0.04447
 0.68205, 0.04659
 0.67214, 0.04866
 0.66235, 0.05071
 0.65269, 0.05272
 0.64318, 0.05469
 0.63378, 0.05663
 0.62452, 0.05853
 0.61537, 0.06038
 0.60636, 0.06219
 0.59747, 0.06397
 0.58869, 0.06569
 0.58004, 0.06738
 0.57150, 0.06902
 0.56308, 0.07061
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 0.52268, 0.07791
 0.51492, 0.07924
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 0.49230, 0.08292
 0.48497, 0.08406
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 0.44301, 0.08998
 0.43633, 0.09082
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 0.41056, 0.09378
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 0.19517, 0.08912
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 0.15941, 0.08231
 0.15637, 0.08164
 0.15337, 0.08098
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 0.13883, 0.07755
 0.13602, 0.07685
 0.13324, 0.07615
 0.13048, 0.07544
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 0.12506, 0.07401
 0.12240, 0.07328
 0.11977, 0.07255
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 0.11457, 0.07108
 0.11203, 0.07034
 0.10950, 0.06959
 0.10700, 0.06884
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 0.09490, 0.06501
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 0.07686, 0.05863
 0.07471, 0.05781
 0.07258, 0.05699
 0.07048, 0.05616
 0.06840, 0.05533
 0.06634, 0.05450
 0.06430, 0.05366
 0.06229, 0.05281
 0.06030, 0.05196
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 0.05638, 0.05025
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 0.05254, 0.04851
 0.05065, 0.04763
 0.04878, 0.04675
 0.04694, 0.04587
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 0.04331, 0.04408
 0.04152, 0.04317
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 0.03290, 0.03854
 0.03123, 0.03758
 0.02959, 0.03662
 0.02796, 0.03565
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 0.00160, 0.01308
 0.00058, 0.01132
-0.00031, 0.00926
-0.00094, 0.00659
-0.00097, 0.00385
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