ファイルインデックス名　: File Index Name        : 1222        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N06-0005-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 8-H-12
翼型ファイル番号　　　　: Airfoil File No.       : 1222
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
 0.98710,-0.00108
 0.97419,-0.00158
 0.96128,-0.00157
 0.94841,-0.00111
 0.93559,-0.00029
 0.92285, 0.00083
 0.91020, 0.00220
 0.89766, 0.00373
 0.88528, 0.00533
 0.87302, 0.00704
 0.86089, 0.00884
 0.84890, 0.01073
 0.83704, 0.01266
 0.82533, 0.01465
 0.81376, 0.01668
 0.80232, 0.01874
 0.79102, 0.02083
 0.77986, 0.02293
 0.76884, 0.02505
 0.75796, 0.02717
 0.74720, 0.02930
 0.73659, 0.03143
 0.72612, 0.03355
 0.71577, 0.03566
 0.70557, 0.03775
 0.69550, 0.03982
 0.68556, 0.04185
 0.67575, 0.04386
 0.66606, 0.04585
 0.65650, 0.04780
 0.64708, 0.04973
 0.63778, 0.05161
 0.62861, 0.05347
 0.61954, 0.05529
 0.61061, 0.05707
 0.60180, 0.05881
 0.59310, 0.06052
 0.58453, 0.06217
 0.57605, 0.06380
 0.56770, 0.06537
 0.55947, 0.06692
 0.55133, 0.06841
 0.54331, 0.06987
 0.53540, 0.07129
 0.52759, 0.07265
 0.51989, 0.07398
 0.51228, 0.07527
 0.50479, 0.07651
 0.49739, 0.07771
 0.49010, 0.07886
 0.48290, 0.07997
 0.47580, 0.08104
 0.46879, 0.08206
 0.46188, 0.08305
 0.45505, 0.08400
 0.44832, 0.08492
 0.44166, 0.08579
 0.43510, 0.08663
 0.42864, 0.08743
 0.42225, 0.08819
 0.41595, 0.08890
 0.40973, 0.08959
 0.40358, 0.09023
 0.39753, 0.09084
 0.39156, 0.09140
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 0.35187, 0.09431
 0.34650, 0.09457
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 0.31573, 0.09539
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 0.30600, 0.09539
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 0.29652, 0.09526
 0.29187, 0.09515
 0.28730, 0.09499
 0.28278, 0.09481
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 0.25267, 0.09288
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 0.21752, 0.08914
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 0.21020, 0.08815
 0.20660, 0.08765
 0.20305, 0.08712
 0.19954, 0.08659
 0.19606, 0.08605
 0.19263, 0.08550
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 0.18587, 0.08438
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 0.16961, 0.08144
 0.16647, 0.08082
 0.16336, 0.08021
 0.16028, 0.07958
 0.15724, 0.07895
 0.15423, 0.07831
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 0.14831, 0.07701
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 0.14251, 0.07570
 0.13966, 0.07504
 0.13684, 0.07437
 0.13404, 0.07370
 0.13127, 0.07302
 0.12853, 0.07234
 0.12583, 0.07165
 0.12316, 0.07096
 0.12051, 0.07026
 0.11788, 0.06956
 0.11529, 0.06885
 0.11272, 0.06814
 0.11019, 0.06743
 0.10767, 0.06671
 0.10519, 0.06597
 0.10273, 0.06524
 0.10029, 0.06451
 0.09788, 0.06376
 0.09549, 0.06302
 0.09313, 0.06226
 0.09080, 0.06150
 0.08849, 0.06074
 0.08621, 0.05997
 0.08394, 0.05920
 0.08171, 0.05842
 0.07949, 0.05764
 0.07730, 0.05686
 0.07513, 0.05606
 0.07298, 0.05526
 0.07086, 0.05446
 0.06876, 0.05366
 0.06668, 0.05284
 0.06462, 0.05203
 0.06258, 0.05121
 0.06057, 0.05038
 0.05858, 0.04955
 0.05660, 0.04872
 0.05465, 0.04787
 0.05271, 0.04703
 0.05081, 0.04618
 0.04892, 0.04532
 0.04705, 0.04445
 0.04520, 0.04358
 0.04336, 0.04270
 0.04155, 0.04181
 0.03976, 0.04092
 0.03799, 0.04002
 0.03625, 0.03912
 0.03451, 0.03820
 0.03280, 0.03727
 0.03111, 0.03634
 0.02944, 0.03539
 0.02778, 0.03443
 0.02616, 0.03347
 0.02455, 0.03248
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 0.02139, 0.03047
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 0.01534, 0.02621
 0.01388, 0.02510
 0.01245, 0.02395
 0.01104, 0.02277
 0.00966, 0.02157
 0.00831, 0.02032
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 0.00445, 0.01625
 0.00324, 0.01477
 0.00207, 0.01321
 0.00098, 0.01145
 0.00000, 0.00941
-0.00074, 0.00674
-0.00086, 0.00396
 0.00000, 0.00000
 0.00000, 0.00000
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 0.03577,-0.01503
 0.03780,-0.01532
 0.03983,-0.01560
 0.04186,-0.01587
 0.04392,-0.01612
 0.04598,-0.01636
 0.04806,-0.01659
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 0.05225,-0.01702
 0.05437,-0.01723
 0.05650,-0.01743
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 0.06079,-0.01779
 0.06296,-0.01796
 0.06516,-0.01813
 0.06737,-0.01830
 0.06958,-0.01846
 0.07182,-0.01861
 0.07407,-0.01876
 0.07634,-0.01892
 0.07863,-0.01906
 0.08093,-0.01921
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 0.08797,-0.01964
 0.09034,-0.01977
 0.09274,-0.01991
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 0.09760,-0.02017
 0.10005,-0.02030
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 0.10503,-0.02056
 0.10755,-0.02068
 0.11009,-0.02080
 0.11264,-0.02091
 0.11522,-0.02102
 0.11782,-0.02113
 0.12044,-0.02124
 0.12309,-0.02134
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 0.13116,-0.02165
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 0.14792,-0.02221
 0.15079,-0.02230
 0.15370,-0.02238
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 0.17787,-0.02300
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 1.00000, 0.00000