NACA 0010-66 (naca001066-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 0010-66 (naca001066-il) Reynolds number: 1,000,000 Max Cl/Cd: 53.61 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca001066-il-1000000.txt Download as CSV file: xf-naca001066-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 0010-66
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0137 0.09712 0.09509 -0.0381 1.0000 0.0096
-16.500 -1.1347 0.06734 0.06502 -0.0552 1.0000 0.0090
-16.250 -1.1877 0.05424 0.05164 -0.0633 1.0000 0.0089
-16.000 -1.2176 0.04901 0.04623 -0.0626 1.0000 0.0088
-15.750 -1.2398 0.04547 0.04254 -0.0599 1.0000 0.0089
-15.500 -1.2587 0.04265 0.03957 -0.0562 1.0000 0.0089
-15.250 -1.2740 0.04035 0.03713 -0.0520 1.0000 0.0090
-15.000 -1.2860 0.03847 0.03511 -0.0476 1.0000 0.0091
-14.750 -1.2850 0.03657 0.03305 -0.0455 0.9993 0.0092
-14.500 -1.2799 0.03509 0.03143 -0.0435 0.9986 0.0093
-14.250 -1.2722 0.03383 0.03003 -0.0415 0.9978 0.0094
-14.000 -1.2865 0.03082 0.02672 -0.0367 0.9964 0.0097
-13.750 -1.2818 0.02923 0.02499 -0.0340 0.9955 0.0100
-13.500 -1.2694 0.02822 0.02388 -0.0324 0.9948 0.0103
-13.250 -1.2542 0.02743 0.02301 -0.0310 0.9943 0.0106
-13.000 -1.2468 0.02673 0.02222 -0.0277 0.9924 0.0109
-12.750 -1.2357 0.02605 0.02145 -0.0251 0.9909 0.0112
-12.500 -1.2228 0.02535 0.02065 -0.0228 0.9894 0.0115
-12.250 -1.2081 0.02465 0.01984 -0.0209 0.9882 0.0118
-12.000 -1.1895 0.02400 0.01907 -0.0197 0.9872 0.0121
-11.750 -1.1679 0.02343 0.01839 -0.0191 0.9864 0.0124
-11.500 -1.1532 0.02195 0.01675 -0.0174 0.9856 0.0131
-11.250 -1.1296 0.02147 0.01623 -0.0172 0.9851 0.0137
-11.000 -1.1043 0.02114 0.01587 -0.0172 0.9847 0.0142
-10.750 -1.0784 0.02086 0.01553 -0.0174 0.9843 0.0149
-10.500 -1.0735 0.02055 0.01517 -0.0127 0.9810 0.0153
-10.250 -1.0546 0.02027 0.01481 -0.0111 0.9793 0.0157
-10.000 -1.0361 0.01951 0.01395 -0.0096 0.9780 0.0164
-9.750 -1.0143 0.01893 0.01334 -0.0088 0.9770 0.0172
-9.500 -0.9888 0.01870 0.01310 -0.0088 0.9761 0.0180
-9.250 -0.9632 0.01846 0.01281 -0.0087 0.9754 0.0187
-9.000 -0.9374 0.01818 0.01248 -0.0086 0.9748 0.0196
-8.750 -0.9102 0.01805 0.01231 -0.0088 0.9743 0.0202
-8.500 -0.8868 0.01723 0.01141 -0.0083 0.9738 0.0214
-8.250 -0.8604 0.01690 0.01106 -0.0085 0.9734 0.0224
-8.000 -0.8331 0.01667 0.01083 -0.0087 0.9730 0.0233
-7.750 -0.8056 0.01644 0.01056 -0.0090 0.9726 0.0243
-7.500 -0.8046 0.01628 0.01036 -0.0031 0.9684 0.0248
-7.250 -0.7835 0.01614 0.01019 -0.0018 0.9666 0.0256
-7.000 -0.7597 0.01606 0.01008 -0.0011 0.9654 0.0260
-6.750 -0.7396 0.01508 0.00901 0.0002 0.9645 0.0277
-6.500 -0.7151 0.01474 0.00866 0.0007 0.9637 0.0288
-6.250 -0.6893 0.01449 0.00841 0.0008 0.9631 0.0299
-6.000 -0.6629 0.01426 0.00815 0.0009 0.9625 0.0311
-5.750 -0.6361 0.01402 0.00788 0.0009 0.9620 0.0320
-5.500 -0.6087 0.01383 0.00767 0.0008 0.9615 0.0327
-5.250 -0.5817 0.01352 0.00731 0.0007 0.9611 0.0338
-5.000 -0.5548 0.01313 0.00690 0.0007 0.9606 0.0356
-4.750 -0.5265 0.01289 0.00666 0.0004 0.9602 0.0373
-4.500 -0.4978 0.01273 0.00649 0.0000 0.9598 0.0391
-4.250 -0.5043 0.01273 0.00646 0.0078 0.9545 0.0398
-4.000 -0.4828 0.01260 0.00631 0.0090 0.9530 0.0412
-3.750 -0.4591 0.01243 0.00613 0.0098 0.9518 0.0437
-3.500 -0.4337 0.01222 0.00597 0.0102 0.9509 0.0498
-3.250 -0.4077 0.01197 0.00582 0.0105 0.9501 0.0682
-3.000 -0.3823 0.01170 0.00571 0.0107 0.9494 0.1024
-2.750 -0.3563 0.01150 0.00564 0.0109 0.9489 0.1303
-2.500 -0.3301 0.01130 0.00557 0.0111 0.9483 0.1640
-2.250 -0.3047 0.01102 0.00551 0.0113 0.9478 0.2154
-2.000 -0.2799 0.01074 0.00547 0.0117 0.9473 0.2787
-1.750 -0.2561 0.01041 0.00543 0.0123 0.9468 0.3546
-1.500 -0.2609 0.01023 0.00546 0.0196 0.9411 0.4166
-1.250 -0.2499 0.00943 0.00525 0.0231 0.9381 0.5696
-1.000 -0.2438 0.00806 0.00518 0.0286 0.9359 0.8951
-0.750 -0.1998 0.00792 0.00505 0.0253 0.9347 0.9176
-0.500 -0.1417 0.00791 0.00506 0.0189 0.9341 0.9273
-0.250 -0.0722 0.00737 0.00449 0.0099 0.9334 0.9328
0.000 0.0000 0.00721 0.00433 0.0000 0.9332 0.9332
0.250 0.0728 0.00736 0.00448 -0.0101 0.9328 0.9333
0.500 0.1420 0.00791 0.00506 -0.0189 0.9273 0.9342
0.750 0.1997 0.00792 0.00505 -0.0253 0.9176 0.9347
1.000 0.2445 0.00805 0.00517 -0.0288 0.8939 0.9359
1.250 0.2501 0.00943 0.00525 -0.0232 0.5706 0.9381
1.500 0.2609 0.01022 0.00546 -0.0196 0.4176 0.9412
1.750 0.2561 0.01041 0.00543 -0.0123 0.3546 0.9468
2.000 0.2799 0.01074 0.00546 -0.0117 0.2781 0.9473
2.250 0.3047 0.01102 0.00551 -0.0113 0.2150 0.9478
2.500 0.3302 0.01129 0.00556 -0.0111 0.1644 0.9483
2.750 0.3563 0.01150 0.00564 -0.0109 0.1302 0.9489
3.000 0.3823 0.01170 0.00571 -0.0108 0.1024 0.9494
3.250 0.4076 0.01197 0.00581 -0.0104 0.0680 0.9501
3.500 0.4336 0.01222 0.00597 -0.0102 0.0497 0.9509
3.750 0.4590 0.01243 0.00613 -0.0098 0.0437 0.9519
4.000 0.4828 0.01260 0.00631 -0.0090 0.0411 0.9530
4.250 0.5042 0.01273 0.00645 -0.0077 0.0398 0.9545
4.500 0.4979 0.01272 0.00649 0.0000 0.0391 0.9598
4.750 0.5266 0.01289 0.00666 -0.0004 0.0373 0.9602
5.000 0.5549 0.01313 0.00689 -0.0008 0.0356 0.9606
5.250 0.5818 0.01352 0.00731 -0.0008 0.0338 0.9611
5.500 0.6088 0.01383 0.00767 -0.0008 0.0327 0.9615
5.750 0.6362 0.01401 0.00788 -0.0009 0.0320 0.9620
6.000 0.6629 0.01426 0.00815 -0.0009 0.0311 0.9625
6.250 0.6893 0.01449 0.00841 -0.0008 0.0299 0.9631
6.500 0.7151 0.01473 0.00866 -0.0007 0.0288 0.9638
6.750 0.7396 0.01507 0.00900 -0.0002 0.0277 0.9646
7.000 0.7597 0.01605 0.01006 0.0011 0.0260 0.9654
7.250 0.7836 0.01611 0.01015 0.0018 0.0255 0.9666
7.500 0.8044 0.01626 0.01034 0.0031 0.0248 0.9684
7.750 0.8056 0.01642 0.01055 0.0090 0.0243 0.9726
8.000 0.8331 0.01666 0.01082 0.0087 0.0233 0.9730
8.250 0.8604 0.01688 0.01105 0.0085 0.0224 0.9734
8.500 0.8867 0.01723 0.01141 0.0083 0.0214 0.9739
8.750 0.9103 0.01803 0.01229 0.0088 0.0202 0.9743
9.000 0.9373 0.01818 0.01249 0.0086 0.0196 0.9748
9.250 0.9632 0.01845 0.01281 0.0087 0.0187 0.9754
9.500 0.9887 0.01870 0.01309 0.0088 0.0180 0.9761
9.750 1.0143 0.01892 0.01333 0.0088 0.0172 0.9770
10.000 1.0361 0.01950 0.01394 0.0096 0.0164 0.9780
10.250 1.0546 0.02026 0.01480 0.0111 0.0157 0.9794
10.500 1.0736 0.02052 0.01513 0.0126 0.0153 0.9810
10.750 1.0787 0.02085 0.01552 0.0173 0.0148 0.9843
11.000 1.1046 0.02113 0.01586 0.0172 0.0142 0.9847
11.250 1.1300 0.02146 0.01622 0.0171 0.0136 0.9851
11.500 1.1535 0.02195 0.01675 0.0173 0.0131 0.9856
11.750 1.1684 0.02343 0.01839 0.0190 0.0123 0.9864
12.000 1.1901 0.02400 0.01907 0.0196 0.0121 0.9872
12.250 1.2086 0.02466 0.01985 0.0208 0.0118 0.9882
12.500 1.2234 0.02535 0.02065 0.0227 0.0115 0.9895
12.750 1.2365 0.02602 0.02142 0.0249 0.0112 0.9909
13.000 1.2471 0.02675 0.02225 0.0276 0.0109 0.9925
13.250 1.2548 0.02744 0.02303 0.0309 0.0106 0.9943
13.500 1.2703 0.02821 0.02388 0.0322 0.0103 0.9948
13.750 1.2829 0.02922 0.02498 0.0338 0.0100 0.9955
14.000 1.2872 0.03085 0.02676 0.0365 0.0097 0.9965
14.250 1.2731 0.03384 0.03004 0.0413 0.0094 0.9978
14.500 1.2809 0.03509 0.03143 0.0432 0.0093 0.9986
14.750 1.2858 0.03659 0.03308 0.0453 0.0092 0.9994
15.000 1.2867 0.03843 0.03507 0.0475 0.0091 1.0000
15.250 1.2746 0.04032 0.03710 0.0520 0.0090 1.0000
15.500 1.2589 0.04265 0.03957 0.0562 0.0089 1.0000
15.750 1.2408 0.04539 0.04246 0.0598 0.0089 1.0000
16.000 1.2172 0.04905 0.04628 0.0626 0.0088 1.0000
16.250 1.1882 0.05419 0.05159 0.0633 0.0089 1.0000
16.500 1.1295 0.06881 0.06651 0.0539 0.0090 1.0000
16.750 1.0135 0.09727 0.09525 0.0379 0.0096 1.0000
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