ファイルインデックス名　: File Index Name        : 0747        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N09-0020-1
翼型名　　　　　　　　　: Airfoil Name           : Naylor & Griffiths 20
翼型ファイル番号　　　　: Airfoil File No.       : 0747
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-A01E


座標　　　　　　　　　　: Plot Ordinates         :

 X             Y

 1.00000, 0.00000
 0.98671, 0.00398
 0.97362, 0.00720
 0.96072, 0.00977
 0.94801, 0.01178
 0.93549, 0.01333
 0.92315, 0.01450
 0.91099, 0.01538
 0.89900, 0.01608
 0.88719, 0.01707
 0.87554, 0.01801
 0.86406, 0.01891
 0.85274, 0.01977
 0.84158, 0.02060
 0.83058, 0.02140
 0.81973, 0.02216
 0.80903, 0.02289
 0.79848, 0.02360
 0.78808, 0.02429
 0.77781, 0.02496
 0.76769, 0.02560
 0.75770, 0.02622
 0.74785, 0.02682
 0.73814, 0.02739
 0.72855, 0.02794
 0.71909, 0.02847
 0.70976, 0.02898
 0.70055, 0.02947
 0.69146, 0.02995
 0.68249, 0.03041
 0.67363, 0.03085
 0.66490, 0.03127
 0.65627, 0.03168
 0.64776, 0.03207
 0.63935, 0.03244
 0.63106, 0.03279
 0.62287, 0.03313
 0.61478, 0.03345
 0.60680, 0.03375
 0.59891, 0.03404
 0.59112, 0.03429
 0.58344, 0.03452
 0.57584, 0.03474
 0.56834, 0.03495
 0.56094, 0.03515
 0.55362, 0.03533
 0.54639, 0.03551
 0.53925, 0.03568
 0.53220, 0.03584
 0.52523, 0.03599
 0.51835, 0.03613
 0.51155, 0.03627
 0.50483, 0.03641
 0.49819, 0.03654
 0.49163, 0.03670
 0.48514, 0.03685
 0.47874, 0.03700
 0.47240, 0.03714
 0.46614, 0.03728
 0.45996, 0.03741
 0.45384, 0.03754
 0.44780, 0.03766
 0.44182, 0.03778
 0.43591, 0.03790
 0.43007, 0.03801
 0.42430, 0.03811
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 0.40185, 0.03847
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 0.39099, 0.03862
 0.38566, 0.03868
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 0.34501, 0.03898
 0.34017, 0.03900
 0.33538, 0.03901
 0.33065, 0.03901
 0.32596, 0.03901
 0.32133, 0.03900
 0.31674, 0.03899
 0.31220, 0.03897
 0.30771, 0.03895
 0.30326, 0.03892
 0.29887, 0.03889
 0.29451, 0.03886
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 0.28594, 0.03878
 0.28172, 0.03874
 0.27754, 0.03870
 0.27340, 0.03865
 0.26931, 0.03859
 0.26526, 0.03854
 0.26125, 0.03848
 0.25728, 0.03842
 0.25334, 0.03835
 0.24945, 0.03828
 0.24560, 0.03821
 0.24178, 0.03813
 0.23800, 0.03805
 0.23426, 0.03797
 0.23056, 0.03788
 0.22689, 0.03779
 0.22326, 0.03770
 0.21966, 0.03761
 0.21610, 0.03751
 0.21257, 0.03740
 0.20907, 0.03730
 0.20561, 0.03719
 0.20218, 0.03707
 0.19879, 0.03696
 0.19542, 0.03684
 0.19209, 0.03672
 0.18879, 0.03659
 0.18552, 0.03646
 0.18228, 0.03633
 0.17908, 0.03619
 0.17590, 0.03605
 0.17275, 0.03590
 0.16963, 0.03576
 0.16654, 0.03560
 0.16348, 0.03545
 0.16044, 0.03529
 0.15743, 0.03513
 0.15445, 0.03496
 0.15150, 0.03479
 0.14858, 0.03461
 0.14568, 0.03443
 0.14280, 0.03424
 0.13996, 0.03405
 0.13713, 0.03386
 0.13434, 0.03366
 0.13157, 0.03346
 0.12882, 0.03325
 0.12610, 0.03304
 0.12340, 0.03282
 0.12072, 0.03261
 0.11807, 0.03238
 0.11544, 0.03216
 0.11283, 0.03193
 0.11025, 0.03169
 0.10769, 0.03145
 0.10515, 0.03121
 0.10264, 0.03097
 0.10014, 0.03071
 0.09767, 0.03048
 0.09521, 0.03023
 0.09278, 0.02998
 0.09037, 0.02972
 0.08798, 0.02946
 0.08561, 0.02919
 0.08326, 0.02890
 0.08093, 0.02861
 0.07862, 0.02831
 0.07633, 0.02799
 0.07405, 0.02765
 0.07180, 0.02729
 0.06956, 0.02691
 0.06735, 0.02652
 0.06515, 0.02611
 0.06297, 0.02570
 0.06081, 0.02527
 0.05866, 0.02483
 0.05653, 0.02438
 0.05442, 0.02392
 0.05233, 0.02344
 0.05026, 0.02296
 0.04820, 0.02246
 0.04615, 0.02195
 0.04413, 0.02144
 0.04212, 0.02091
 0.04012, 0.02037
 0.03815, 0.01982
 0.03618, 0.01926
 0.03424, 0.01870
 0.03231, 0.01812
 0.03039, 0.01753
 0.02849, 0.01693
 0.02660, 0.01633
 0.02473, 0.01571
 0.02287, 0.01512
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 0.01920, 0.01388
 0.01739, 0.01323
 0.01559, 0.01256
 0.01380, 0.01184
 0.01203, 0.01110
 0.01027, 0.01029
 0.00853, 0.00943
 0.00680, 0.00847
 0.00508, 0.00737
 0.00337, 0.00606
 0.00168, 0.00433
 0.00056, 0.00254
 0.00000, 0.00000
 0.00000, 0.00000
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 0.02287,-0.00650
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 0.03815,-0.00826
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 0.04615,-0.00890
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