ファイルインデックス名　: File Index Name        : 0791        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : R01-0020-1
翼型名　　　　　　　　　: Airfoil Name           : R.A.F. 20
翼型ファイル番号　　　　: Airfoil File No.       : 0791
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.   : X68eB03-C01G3


座標　　　　　　　　　　: Plot Ordinates         :

 X             Y

 1.00000, 0.00000
 0.98671, 0.00345
 0.97362, 0.00645
 0.96072, 0.00906
 0.94801, 0.01134
 0.93549, 0.01333
 0.92315, 0.01510
 0.91099, 0.01668
 0.89900, 0.01814
 0.88719, 0.01975
 0.87554, 0.02132
 0.86406, 0.02285
 0.85274, 0.02434
 0.84158, 0.02579
 0.83058, 0.02720
 0.81973, 0.02857
 0.80903, 0.02990
 0.79848, 0.03118
 0.78808, 0.03242
 0.77781, 0.03361
 0.76769, 0.03477
 0.75770, 0.03590
 0.74785, 0.03699
 0.73814, 0.03804
 0.72855, 0.03906
 0.71909, 0.04005
 0.70976, 0.04101
 0.70055, 0.04194
 0.69146, 0.04286
 0.68249, 0.04374
 0.67363, 0.04460
 0.66490, 0.04543
 0.65627, 0.04623
 0.64776, 0.04701
 0.63935, 0.04775
 0.63106, 0.04847
 0.62287, 0.04916
 0.61478, 0.04983
 0.60680, 0.05047
 0.59891, 0.05108
 0.59112, 0.05165
 0.58344, 0.05220
 0.57584, 0.05272
 0.56834, 0.05322
 0.56094, 0.05370
 0.55362, 0.05416
 0.54639, 0.05459
 0.53925, 0.05500
 0.53220, 0.05540
 0.52523, 0.05577
 0.51835, 0.05612
 0.51155, 0.05646
 0.50483, 0.05678
 0.49819, 0.05708
 0.49163, 0.05737
 0.48514, 0.05764
 0.47874, 0.05789
 0.47240, 0.05813
 0.46614, 0.05835
 0.45996, 0.05856
 0.45384, 0.05876
 0.44780, 0.05894
 0.44182, 0.05911
 0.43591, 0.05927
 0.43007, 0.05941
 0.42430, 0.05955
 0.41859, 0.05967
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 0.40737, 0.05988
 0.40185, 0.05997
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 0.39099, 0.06015
 0.38566, 0.06023
 0.38038, 0.06030
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 0.32596, 0.06040
 0.32133, 0.06035
 0.31674, 0.06030
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 0.30771, 0.06016
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 0.25334, 0.05815
 0.24945, 0.05794
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 0.23800, 0.05725
 0.23426, 0.05700
 0.23056, 0.05675
 0.22689, 0.05650
 0.22326, 0.05623
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 0.21257, 0.05539
 0.20907, 0.05510
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 0.19879, 0.05419
 0.19542, 0.05386
 0.19209, 0.05353
 0.18879, 0.05320
 0.18552, 0.05286
 0.18228, 0.05252
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 0.17275, 0.05145
 0.16963, 0.05109
 0.16654, 0.05072
 0.16348, 0.05034
 0.16044, 0.04996
 0.15743, 0.04958
 0.15445, 0.04919
 0.15150, 0.04880
 0.14858, 0.04841
 0.14568, 0.04802
 0.14280, 0.04763
 0.13996, 0.04723
 0.13713, 0.04683
 0.13434, 0.04642
 0.13157, 0.04601
 0.12882, 0.04559
 0.12610, 0.04517
 0.12340, 0.04474
 0.12072, 0.04431
 0.11807, 0.04387
 0.11544, 0.04343
 0.11283, 0.04298
 0.11025, 0.04252
 0.10769, 0.04206
 0.10515, 0.04159
 0.10264, 0.04111
 0.10014, 0.04063
 0.09767, 0.04014
 0.09521, 0.03965
 0.09278, 0.03915
 0.09037, 0.03864
 0.08798, 0.03812
 0.08561, 0.03758
 0.08326, 0.03704
 0.08093, 0.03649
 0.07862, 0.03592
 0.07633, 0.03534
 0.07405, 0.03474
 0.07180, 0.03412
 0.06956, 0.03348
 0.06735, 0.03282
 0.06515, 0.03215
 0.06297, 0.03147
 0.06081, 0.03078
 0.05866, 0.03007
 0.05653, 0.02934
 0.05442, 0.02861
 0.05233, 0.02786
 0.05026, 0.02710
 0.04820, 0.02632
 0.04615, 0.02552
 0.04413, 0.02471
 0.04212, 0.02389
 0.04012, 0.02305
 0.03815, 0.02220
 0.03618, 0.02133
 0.03424, 0.02046
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 0.03039, 0.01866
 0.02849, 0.01775
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 0.02473, 0.01586
 0.02287, 0.01488
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 0.01739, 0.01187
 0.01559, 0.01084
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 0.00853, 0.00652
 0.00680, 0.00538
 0.00508, 0.00422
 0.00337, 0.00300
 0.00168, 0.00172
 0.00056, 0.00075
 0.00000, 0.00000
 0.00000, 0.00000
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 0.11025,-0.01085
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 1.00000, 0.00000