E176 (8.83%) (e176-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E176 (8.83%) (e176-il) Reynolds number: 50,000 Max Cl/Cd: 38.69 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e176-il-50000-n5.txt Download as CSV file: xf-e176-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E176 (8.83%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3942 0.10489 0.09825 -0.0191 1.0000 0.1067
-8.500 -0.3906 0.10170 0.09512 -0.0207 1.0000 0.1087
-8.250 -0.3991 0.09965 0.09321 -0.0244 1.0000 0.1133
-7.750 -0.3931 0.08774 0.08137 -0.0316 1.0000 0.0587
-7.500 -0.3871 0.08418 0.07787 -0.0325 1.0000 0.0575
-7.250 -0.3834 0.08036 0.07412 -0.0351 1.0000 0.0570
-7.000 -0.3787 0.07657 0.07039 -0.0374 1.0000 0.0557
-6.750 -0.3745 0.07258 0.06645 -0.0401 1.0000 0.0549
-6.500 -0.3706 0.06855 0.06241 -0.0425 1.0000 0.0540
-6.250 -0.3678 0.06466 0.05853 -0.0443 1.0000 0.0526
-6.000 -0.3668 0.06079 0.05464 -0.0454 1.0000 0.0514
-5.750 -0.3673 0.05694 0.05068 -0.0460 1.0000 0.0497
-5.250 -0.3304 0.04711 0.03986 -0.0529 0.9864 0.0462
-5.000 -0.2971 0.04262 0.03490 -0.0571 0.9746 0.0459
-4.750 -0.2625 0.03861 0.03031 -0.0607 0.9636 0.0457
-4.500 -0.2256 0.03507 0.02614 -0.0639 0.9541 0.0459
-4.250 -0.1890 0.03215 0.02259 -0.0663 0.9445 0.0463
-4.000 -0.1543 0.02964 0.01967 -0.0681 0.9346 0.0475
-3.750 -0.1190 0.02789 0.01770 -0.0700 0.9257 0.0517
-3.500 -0.0841 0.02642 0.01580 -0.0712 0.9162 0.0577
-3.250 -0.0517 0.02498 0.01412 -0.0718 0.9063 0.0620
-3.000 -0.0173 0.02377 0.01271 -0.0728 0.8977 0.0696
-2.750 0.0147 0.02272 0.01148 -0.0734 0.8881 0.0862
-2.500 0.0440 0.02153 0.01063 -0.0741 0.8782 0.1528
-2.250 0.0711 0.01988 0.01009 -0.0746 0.8697 0.3625
-2.000 0.0881 0.01858 0.01001 -0.0715 0.8603 0.6549
-1.750 0.1540 0.01778 0.00922 -0.0770 0.8554 1.0000
-1.500 0.1810 0.01794 0.00894 -0.0769 0.8454 1.0000
-1.250 0.2065 0.01815 0.00879 -0.0766 0.8352 1.0000
-1.000 0.2333 0.01834 0.00866 -0.0765 0.8263 1.0000
-0.750 0.2595 0.01855 0.00857 -0.0762 0.8174 1.0000
-0.500 0.2842 0.01882 0.00860 -0.0758 0.8080 1.0000
-0.250 0.3115 0.01902 0.00857 -0.0756 0.8005 1.0000
0.000 0.3356 0.01933 0.00871 -0.0751 0.7912 1.0000
0.250 0.3611 0.01961 0.00882 -0.0747 0.7831 1.0000
0.500 0.3873 0.01989 0.00895 -0.0745 0.7752 1.0000
0.750 0.4122 0.02024 0.00919 -0.0742 0.7668 1.0000
1.000 0.4391 0.02051 0.00934 -0.0739 0.7599 1.0000
1.250 0.4631 0.02092 0.00970 -0.0735 0.7512 1.0000
1.500 0.4904 0.02117 0.00987 -0.0732 0.7449 1.0000
1.750 0.5137 0.02165 0.01032 -0.0728 0.7359 1.0000
2.000 0.5406 0.02193 0.01058 -0.0725 0.7296 1.0000
2.250 0.5639 0.02243 0.01109 -0.0721 0.7208 1.0000
2.500 0.5896 0.02280 0.01146 -0.0717 0.7137 1.0000
2.750 0.6139 0.02324 0.01194 -0.0712 0.7055 1.0000
3.000 0.6382 0.02370 0.01248 -0.0708 0.6975 1.0000
3.250 0.6637 0.02407 0.01290 -0.0703 0.6900 1.0000
3.500 0.6866 0.02461 0.01353 -0.0698 0.6808 1.0000
3.750 0.7140 0.02483 0.01381 -0.0692 0.6741 1.0000
4.000 0.7358 0.02542 0.01453 -0.0685 0.6635 1.0000
4.250 0.7593 0.02587 0.01515 -0.0678 0.6537 1.0000
4.500 0.7869 0.02598 0.01537 -0.0671 0.6457 1.0000
4.750 0.8089 0.02647 0.01601 -0.0662 0.6339 1.0000
5.000 0.8317 0.02685 0.01656 -0.0652 0.6219 1.0000
5.250 0.8552 0.02711 0.01706 -0.0641 0.6094 1.0000
5.500 0.8791 0.02728 0.01741 -0.0630 0.5961 1.0000
5.750 0.9029 0.02737 0.01770 -0.0617 0.5817 1.0000
6.000 0.9268 0.02736 0.01790 -0.0603 0.5660 1.0000
6.250 0.9516 0.02716 0.01791 -0.0587 0.5489 1.0000
6.500 0.9724 0.02720 0.01825 -0.0570 0.5278 1.0000
6.750 0.9954 0.02691 0.01817 -0.0551 0.5046 1.0000
7.000 1.0148 0.02689 0.01837 -0.0531 0.4760 1.0000
7.250 1.0325 0.02697 0.01866 -0.0509 0.4402 1.0000
7.500 1.0489 0.02711 0.01886 -0.0484 0.3941 1.0000
7.750 1.0606 0.02772 0.01930 -0.0457 0.3310 1.0000
8.000 1.0650 0.02917 0.02028 -0.0427 0.2625 1.0000
8.250 1.0630 0.03139 0.02209 -0.0400 0.2030 1.0000
8.500 1.0572 0.03396 0.02421 -0.0374 0.1505 1.0000
8.750 1.0496 0.03664 0.02647 -0.0351 0.1092 1.0000
9.000 1.0448 0.03945 0.02901 -0.0333 0.0806 1.0000
9.250 1.0428 0.04226 0.03174 -0.0318 0.0640 1.0000
9.500 1.0421 0.04511 0.03457 -0.0305 0.0551 1.0000
9.750 1.0444 0.04777 0.03731 -0.0293 0.0489 1.0000
10.000 1.0491 0.05035 0.03997 -0.0279 0.0447 1.0000
10.250 1.0582 0.05262 0.04245 -0.0267 0.0403 1.0000
10.500 1.0647 0.05511 0.04498 -0.0258 0.0369 1.0000
10.750 1.0786 0.05735 0.04745 -0.0244 0.0341 1.0000
11.000 1.0951 0.05974 0.05019 -0.0230 0.0320 1.0000
11.250 1.1078 0.06272 0.05351 -0.0219 0.0307 1.0000
11.500 1.1142 0.06615 0.05733 -0.0212 0.0300 1.0000
11.750 1.1147 0.07005 0.06154 -0.0210 0.0294 1.0000
12.000 1.1107 0.07436 0.06615 -0.0214 0.0292 1.0000
12.250 1.1024 0.07915 0.07123 -0.0223 0.0290 1.0000
12.500 1.0905 0.08451 0.07686 -0.0238 0.0289 1.0000
12.750 1.0755 0.09049 0.08310 -0.0262 0.0290 1.0000
13.000 1.0580 0.09724 0.09008 -0.0295 0.0292 1.0000
13.250 1.0374 0.10499 0.09804 -0.0338 0.0295 1.0000
13.500 1.0155 0.11388 0.10711 -0.0393 0.0300 1.0000
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Polar data table (+)
Polar graphs
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