ファイルインデックス名　: File Index Name        : 1310        .A  
翼型整理番号　　　　　　: Airfoil Serial No.     : N06-0032-1
翼型名　　　　　　　　　: Airfoil Name           : N.A.C.A. 10-H-12
翼型ファイル番号　　　　: Airfoil File No.       : 1310
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
 0.98702,-0.00100
 0.97401,-0.00124
 0.96097,-0.00082
 0.94796, 0.00017
 0.93498, 0.00163
 0.92207, 0.00347
 0.90925, 0.00562
 0.89653, 0.00795
 0.88397, 0.01039
 0.87152, 0.01295
 0.85921, 0.01562
 0.84704, 0.01837
 0.83502, 0.02115
 0.82314, 0.02398
 0.81140, 0.02684
 0.79981, 0.02971
 0.78836, 0.03259
 0.77707, 0.03546
 0.76592, 0.03831
 0.75492, 0.04114
 0.74406, 0.04393
 0.73336, 0.04667
 0.72282, 0.04936
 0.71241, 0.05200
 0.70214, 0.05461
 0.69202, 0.05715
 0.68204, 0.05963
 0.67219, 0.06206
 0.66249, 0.06441
 0.65292, 0.06670
 0.64351, 0.06890
 0.63422, 0.07103
 0.62508, 0.07307
 0.61605, 0.07504
 0.60717, 0.07695
 0.59842, 0.07876
 0.58979, 0.08051
 0.58129, 0.08218
 0.57291, 0.08375
 0.56465, 0.08526
 0.55653, 0.08668
 0.54852, 0.08800
 0.54063, 0.08925
 0.53288, 0.09040
 0.52522, 0.09148
 0.51768, 0.09247
 0.51026, 0.09338
 0.50295, 0.09421
 0.49576, 0.09492
 0.48868, 0.09556
 0.48171, 0.09612
 0.47484, 0.09662
 0.46806, 0.09705
 0.46139, 0.09741
 0.45480, 0.09774
 0.44832, 0.09800
 0.44191, 0.09822
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 0.42323, 0.09861
 0.41717, 0.09866
 0.41119, 0.09867
 0.40529, 0.09865
 0.39946, 0.09860
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 0.30161, 0.09354
 0.29706, 0.09311
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 0.22340, 0.08390
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 0.21609, 0.08274
 0.21250, 0.08216
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 0.20542, 0.08097
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 0.19850, 0.07976
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 0.19172, 0.07853
 0.18839, 0.07790
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 0.17540, 0.07535
 0.17223, 0.07471
 0.16910, 0.07406
 0.16600, 0.07341
 0.16294, 0.07275
 0.15990, 0.07209
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 0.15394, 0.07075
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 0.14808, 0.06941
 0.14520, 0.06873
 0.14235, 0.06806
 0.13953, 0.06737
 0.13673, 0.06669
 0.13396, 0.06600
 0.13123, 0.06531
 0.12852, 0.06461
 0.12584, 0.06392
 0.12318, 0.06322
 0.12055, 0.06252
 0.11794, 0.06181
 0.11537, 0.06111
 0.11282, 0.06040
 0.11029, 0.05969
 0.10779, 0.05897
 0.10532, 0.05826
 0.10286, 0.05754
 0.10043, 0.05681
 0.09803, 0.05609
 0.09564, 0.05536
 0.09329, 0.05464
 0.09096, 0.05390
 0.08865, 0.05317
 0.08636, 0.05244
 0.08409, 0.05169
 0.08185, 0.05095
 0.07963, 0.05020
 0.07743, 0.04945
 0.07525, 0.04870
 0.07309, 0.04795
 0.07096, 0.04719
 0.06885, 0.04643
 0.06675, 0.04567
 0.06468, 0.04490
 0.06263, 0.04413
 0.06059, 0.04335
 0.05858, 0.04258
 0.05659, 0.04179
 0.05462, 0.04100
 0.05267, 0.04021
 0.05073, 0.03942
 0.04882, 0.03862
 0.04692, 0.03781
 0.04505, 0.03699
 0.04319, 0.03618
 0.04135, 0.03535
 0.03954, 0.03453
 0.03774, 0.03370
 0.03595, 0.03285
 0.03420, 0.03200
 0.03245, 0.03115
 0.03072, 0.03027
 0.02902, 0.02941
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 0.01759, 0.02301
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 0.01449, 0.02107
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 0.01149, 0.01902
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 0.00445, 0.01314
 0.00317, 0.01169
 0.00195, 0.01007
 0.00083, 0.00817
-0.00010, 0.00574
-0.00046, 0.00330
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 0.00000, 0.00000
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 0.04017,-0.01284
 0.04220,-0.01305
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 0.06107,-0.01463
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 0.06544,-0.01492
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 0.11569,-0.01752
 0.11830,-0.01762
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 1.00000, 0.00000