DF 101 AIRFOIL (df101-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DF 101 AIRFOIL (df101-il) Reynolds number: 500,000 Max Cl/Cd: 80.55 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-df101-il-500000-n5.txt Download as CSV file: xf-df101-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DF 101 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.6897 0.07888 0.07618 -0.0395 1.0000 0.0054
-12.750 -0.7199 0.06911 0.06630 -0.0454 1.0000 0.0055
-12.500 -0.7447 0.06061 0.05771 -0.0509 1.0000 0.0054
-12.250 -0.7821 0.04903 0.04591 -0.0600 1.0000 0.0053
-12.000 -0.7969 0.04206 0.03877 -0.0668 1.0000 0.0052
-11.750 -0.8153 0.03726 0.03376 -0.0698 1.0000 0.0052
-11.500 -0.8240 0.03501 0.03136 -0.0685 1.0000 0.0053
-11.250 -0.8403 0.03272 0.02889 -0.0647 1.0000 0.0053
-11.000 -0.8431 0.03091 0.02690 -0.0619 1.0000 0.0054
-10.750 -0.8381 0.02975 0.02561 -0.0594 1.0000 0.0055
-10.500 -0.8381 0.02829 0.02399 -0.0561 1.0000 0.0055
-10.250 -0.8240 0.02556 0.02096 -0.0565 0.9955 0.0057
-10.000 -0.8011 0.02388 0.01907 -0.0573 0.9905 0.0059
-9.750 -0.7751 0.02252 0.01756 -0.0583 0.9863 0.0061
-9.500 -0.7467 0.02131 0.01620 -0.0596 0.9834 0.0063
-9.250 -0.7207 0.02019 0.01493 -0.0601 0.9787 0.0065
-9.000 -0.6931 0.01917 0.01378 -0.0609 0.9744 0.0068
-8.750 -0.6636 0.01820 0.01268 -0.0619 0.9710 0.0071
-8.500 -0.6375 0.01730 0.01163 -0.0621 0.9657 0.0073
-8.250 -0.6103 0.01650 0.01070 -0.0624 0.9604 0.0077
-8.000 -0.5815 0.01576 0.00985 -0.0630 0.9563 0.0080
-7.750 -0.5579 0.01500 0.00899 -0.0625 0.9492 0.0084
-7.500 -0.5316 0.01437 0.00829 -0.0625 0.9435 0.0089
-7.250 -0.5062 0.01389 0.00773 -0.0621 0.9372 0.0095
-7.000 -0.4805 0.01349 0.00727 -0.0618 0.9307 0.0104
-6.750 -0.4547 0.01310 0.00679 -0.0614 0.9247 0.0112
-6.500 -0.4304 0.01260 0.00624 -0.0608 0.9175 0.0124
-6.250 -0.4046 0.01222 0.00580 -0.0604 0.9116 0.0137
-6.000 -0.3794 0.01188 0.00538 -0.0598 0.9042 0.0151
-5.750 -0.3538 0.01149 0.00494 -0.0593 0.8978 0.0172
-5.500 -0.3282 0.01120 0.00459 -0.0589 0.8904 0.0194
-5.250 -0.3023 0.01088 0.00424 -0.0584 0.8835 0.0228
-5.000 -0.2762 0.01062 0.00393 -0.0580 0.8759 0.0263
-4.750 -0.2503 0.01031 0.00361 -0.0576 0.8685 0.0326
-4.500 -0.2247 0.00995 0.00330 -0.0571 0.8603 0.0485
-4.250 -0.1999 0.00949 0.00298 -0.0566 0.8524 0.0874
-4.000 -0.1742 0.00915 0.00275 -0.0562 0.8435 0.1216
-3.750 -0.1482 0.00889 0.00257 -0.0558 0.8348 0.1516
-3.500 -0.1217 0.00871 0.00241 -0.0555 0.8255 0.1749
-3.250 -0.0950 0.00856 0.00228 -0.0552 0.8159 0.1936
-3.000 -0.0684 0.00841 0.00215 -0.0549 0.8061 0.2179
-2.750 -0.0419 0.00826 0.00205 -0.0546 0.7956 0.2452
-2.250 0.0119 0.00807 0.00185 -0.0540 0.7733 0.2782
-2.000 0.0388 0.00800 0.00176 -0.0537 0.7614 0.2922
-1.750 0.0655 0.00794 0.00168 -0.0533 0.7487 0.3076
-1.250 0.1187 0.00782 0.00154 -0.0526 0.7207 0.3433
-1.000 0.1450 0.00777 0.00149 -0.0523 0.7050 0.3657
-0.750 0.1711 0.00772 0.00144 -0.0518 0.6875 0.3910
-0.500 0.1969 0.00767 0.00141 -0.0514 0.6685 0.4221
-0.250 0.2224 0.00760 0.00139 -0.0509 0.6509 0.4610
0.000 0.2480 0.00752 0.00139 -0.0504 0.6353 0.5058
0.250 0.2731 0.00741 0.00140 -0.0498 0.6206 0.5595
0.500 0.2981 0.00732 0.00142 -0.0491 0.6057 0.6127
0.750 0.3227 0.00722 0.00145 -0.0484 0.5909 0.6679
1.250 0.3689 0.00695 0.00157 -0.0460 0.5608 0.8106
1.500 0.3946 0.00692 0.00169 -0.0452 0.5448 0.8882
1.750 0.4267 0.00703 0.00179 -0.0459 0.5264 0.9288
2.000 0.4607 0.00718 0.00187 -0.0471 0.5062 0.9493
2.250 0.4950 0.00736 0.00196 -0.0485 0.4847 0.9633
2.500 0.5285 0.00754 0.00205 -0.0498 0.4627 0.9728
2.750 0.5620 0.00775 0.00216 -0.0511 0.4370 0.9805
3.000 0.5960 0.00799 0.00227 -0.0525 0.4087 0.9864
3.250 0.6292 0.00825 0.00241 -0.0538 0.3812 0.9922
3.500 0.6634 0.00854 0.00256 -0.0554 0.3508 0.9978
3.750 0.6918 0.00882 0.00272 -0.0558 0.3257 1.0000
4.000 0.7134 0.00907 0.00289 -0.0546 0.3047 1.0000
4.250 0.7351 0.00933 0.00307 -0.0534 0.2853 1.0000
4.500 0.7570 0.00959 0.00325 -0.0523 0.2683 1.0000
4.750 0.7790 0.00984 0.00344 -0.0512 0.2531 1.0000
5.000 0.8010 0.01010 0.00365 -0.0502 0.2386 1.0000
5.250 0.8235 0.01033 0.00385 -0.0491 0.2275 1.0000
5.500 0.8459 0.01058 0.00407 -0.0481 0.2164 1.0000
5.750 0.8681 0.01084 0.00430 -0.0471 0.2060 1.0000
6.000 0.8907 0.01109 0.00454 -0.0461 0.1969 1.0000
6.250 0.9134 0.01134 0.00478 -0.0452 0.1881 1.0000
6.500 0.9357 0.01163 0.00505 -0.0442 0.1789 1.0000
6.750 0.9582 0.01191 0.00531 -0.0433 0.1689 1.0000
7.000 0.9802 0.01223 0.00561 -0.0423 0.1561 1.0000
7.250 1.0021 0.01257 0.00591 -0.0414 0.1439 1.0000
7.500 1.0233 0.01296 0.00623 -0.0403 0.1294 1.0000
7.750 1.0443 0.01335 0.00658 -0.0392 0.1159 1.0000
8.000 1.0654 0.01374 0.00694 -0.0382 0.1048 1.0000
8.250 1.0860 0.01417 0.00734 -0.0371 0.0938 1.0000
8.500 1.1060 0.01463 0.00776 -0.0359 0.0825 1.0000
8.750 1.1250 0.01514 0.00823 -0.0346 0.0699 1.0000
9.000 1.1424 0.01577 0.00878 -0.0330 0.0551 1.0000
9.250 1.1583 0.01648 0.00941 -0.0313 0.0411 1.0000
9.500 1.1737 0.01719 0.01009 -0.0295 0.0300 1.0000
9.750 1.1888 0.01788 0.01076 -0.0276 0.0230 1.0000
10.000 1.2021 0.01855 0.01144 -0.0254 0.0186 1.0000
10.250 1.2152 0.01918 0.01210 -0.0232 0.0164 1.0000
10.500 1.2270 0.01990 0.01286 -0.0208 0.0147 1.0000
10.750 1.2403 0.02054 0.01358 -0.0188 0.0139 1.0000
11.000 1.2531 0.02122 0.01434 -0.0169 0.0132 1.0000
11.250 1.2646 0.02201 0.01520 -0.0148 0.0124 1.0000
11.500 1.2748 0.02291 0.01616 -0.0127 0.0117 1.0000
11.750 1.2826 0.02399 0.01731 -0.0105 0.0110 1.0000
12.000 1.2911 0.02504 0.01845 -0.0086 0.0107 1.0000
12.250 1.3000 0.02610 0.01961 -0.0068 0.0103 1.0000
12.500 1.3077 0.02728 0.02089 -0.0051 0.0102 1.0000
12.750 1.3142 0.02861 0.02232 -0.0034 0.0099 1.0000
13.000 1.3197 0.03008 0.02389 -0.0019 0.0096 1.0000
13.250 1.3243 0.03168 0.02559 -0.0005 0.0092 1.0000
13.500 1.3282 0.03342 0.02744 0.0007 0.0090 1.0000
13.750 1.3301 0.03543 0.02956 0.0017 0.0089 1.0000
14.000 1.3323 0.03753 0.03175 0.0025 0.0086 1.0000
14.250 1.3314 0.04003 0.03436 0.0030 0.0084 1.0000
14.500 1.3258 0.04320 0.03763 0.0032 0.0081 1.0000
14.750 1.3181 0.04680 0.04136 0.0031 0.0079 1.0000
15.000 1.3120 0.05042 0.04510 0.0026 0.0078 1.0000
15.250 1.3061 0.05420 0.04901 0.0017 0.0078 1.0000
15.500 1.3026 0.05787 0.05280 0.0008 0.0077 1.0000
15.750 1.2957 0.06217 0.05724 -0.0006 0.0076 1.0000
16.000 1.2874 0.06684 0.06204 -0.0023 0.0075 1.0000
16.250 1.2780 0.07188 0.06721 -0.0043 0.0074 1.0000
16.500 1.2689 0.07707 0.07253 -0.0066 0.0073 1.0000
16.750 1.2555 0.08310 0.07870 -0.0093 0.0074 1.0000
17.000 1.2446 0.08892 0.08465 -0.0120 0.0072 1.0000
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