ファイルインデックス名　: File Index Name        : 1194        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N04-0099-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 66-206
翼型ファイル番号　　　　: Airfoil File No.       : 1194
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-A01C


座標　　　　　　　　　　: Plot Ordinates         :

 X             Y

 1.00000, 0.00000
 0.98658, 0.00151
 0.97336, 0.00304
 0.96034, 0.00457
 0.94750, 0.00610
 0.93485, 0.00761
 0.92238, 0.00913
 0.91010, 0.01062
 0.89798, 0.01209
 0.88605, 0.01354
 0.87428, 0.01495
 0.86268, 0.01634
 0.85125, 0.01769
 0.83998, 0.01899
 0.82887, 0.02025
 0.81792, 0.02148
 0.80712, 0.02266
 0.79648, 0.02381
 0.78598, 0.02491
 0.77562, 0.02598
 0.76542, 0.02701
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 0.74541, 0.02894
 0.73563, 0.02985
 0.72596, 0.03072
 0.71643, 0.03155
 0.70704, 0.03233
 0.69776, 0.03308
 0.68861, 0.03379
 0.67959, 0.03446
 0.67068, 0.03508
 0.66190, 0.03568
 0.65322, 0.03623
 0.64467, 0.03674
 0.63622, 0.03721
 0.62789, 0.03764
 0.61967, 0.03803
 0.61155, 0.03840
 0.60354, 0.03873
 0.59562, 0.03902
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 0.57250, 0.03971
 0.56498, 0.03989
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 0.52878, 0.04057
 0.52181, 0.04066
 0.51492, 0.04074
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 0.50139, 0.04087
 0.49475, 0.04091
 0.48818, 0.04095
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 0.46269, 0.04099
 0.45651, 0.04097
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 0.23139, 0.03407
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 0.22045, 0.03338
 0.21687, 0.03315
 0.21333, 0.03292
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 0.18293, 0.03073
 0.17971, 0.03047
 0.17653, 0.03023
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 0.17025, 0.02972
 0.16715, 0.02946
 0.16408, 0.02920
 0.16104, 0.02894
 0.15803, 0.02868
 0.15504, 0.02842
 0.15208, 0.02815
 0.14915, 0.02788
 0.14625, 0.02762
 0.14338, 0.02734
 0.14052, 0.02707
 0.13770, 0.02681
 0.13490, 0.02653
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 0.12666, 0.02570
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 0.11863, 0.02486
 0.11600, 0.02457
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 0.09824, 0.02254
 0.09580, 0.02224
 0.09336, 0.02195
 0.09096, 0.02165
 0.08857, 0.02135
 0.08621, 0.02105
 0.08386, 0.02074
 0.08154, 0.02043
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 0.07695, 0.01982
 0.07469, 0.01951
 0.07243, 0.01920
 0.07021, 0.01889
 0.06800, 0.01857
 0.06581, 0.01825
 0.06364, 0.01794
 0.06149, 0.01762
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 0.04290, 0.01461
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 0.00042, 0.00172
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