E221 (9.39%) (e221-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E221 (9.39%) (e221-il) Reynolds number: 50,000 Max Cl/Cd: 33.68 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e221-il-50000-n5.txt Download as CSV file: xf-e221-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E221 (9.39%)
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5238 0.11528 0.10837 0.0034 1.0000 0.0545
-9.750 -0.5206 0.11096 0.10410 0.0016 1.0000 0.0516
-9.500 -0.5368 0.10370 0.09696 -0.0070 1.0000 0.0460
-9.250 -0.5274 0.10015 0.09343 -0.0062 1.0000 0.0451
-9.000 -0.5239 0.09608 0.08940 -0.0075 1.0000 0.0442
-8.750 -0.5230 0.09171 0.08509 -0.0096 1.0000 0.0434
-8.500 -0.5237 0.08714 0.08060 -0.0124 1.0000 0.0427
-8.250 -0.5273 0.08214 0.07567 -0.0160 1.0000 0.0419
-8.000 -0.5320 0.07733 0.07089 -0.0189 1.0000 0.0411
-7.750 -0.5353 0.07225 0.06580 -0.0216 1.0000 0.0404
-7.500 -0.5381 0.06712 0.06059 -0.0238 1.0000 0.0396
-7.250 -0.5391 0.06214 0.05545 -0.0253 1.0000 0.0389
-7.000 -0.5377 0.05730 0.05038 -0.0261 1.0000 0.0383
-6.750 -0.5332 0.05269 0.04546 -0.0262 1.0000 0.0378
-6.500 -0.5256 0.04842 0.04082 -0.0258 1.0000 0.0376
-6.250 -0.5149 0.04460 0.03658 -0.0249 1.0000 0.0376
-6.000 -0.5016 0.04116 0.03272 -0.0239 1.0000 0.0378
-5.750 -0.4860 0.03823 0.02940 -0.0227 1.0000 0.0386
-5.500 -0.4687 0.03569 0.02649 -0.0214 1.0000 0.0408
-5.250 -0.4499 0.03327 0.02357 -0.0200 1.0000 0.0433
-5.000 -0.4294 0.03100 0.02079 -0.0185 1.0000 0.0455
-4.750 -0.4091 0.02886 0.01848 -0.0172 1.0000 0.0474
-4.500 -0.3891 0.02719 0.01672 -0.0158 1.0000 0.0504
-4.250 -0.3689 0.02582 0.01513 -0.0143 1.0000 0.0562
-4.000 -0.3507 0.02459 0.01390 -0.0127 1.0000 0.0641
-3.750 -0.3326 0.02343 0.01268 -0.0111 1.0000 0.0759
-3.500 -0.3147 0.02240 0.01159 -0.0096 1.0000 0.0984
-3.250 -0.2972 0.02126 0.01068 -0.0084 1.0000 0.1408
-3.000 -0.2637 0.01961 0.00978 -0.0105 0.9872 0.2645
-2.750 -0.2320 0.01806 0.00933 -0.0118 0.9726 0.4852
-2.500 -0.1603 0.01694 0.00933 -0.0165 0.9752 0.8664
-2.250 -0.0627 0.01696 0.00869 -0.0289 0.9847 0.9995
-2.000 -0.0176 0.01693 0.00826 -0.0332 0.9622 1.0000
-1.750 0.0264 0.01691 0.00788 -0.0370 0.9417 1.0000
-1.500 0.0667 0.01689 0.00755 -0.0398 0.9209 1.0000
-1.250 0.1046 0.01689 0.00729 -0.0420 0.9015 1.0000
-1.000 0.1369 0.01694 0.00711 -0.0430 0.8819 1.0000
-0.750 0.1652 0.01703 0.00699 -0.0431 0.8626 1.0000
-0.500 0.1915 0.01715 0.00692 -0.0427 0.8446 1.0000
-0.250 0.2160 0.01729 0.00689 -0.0419 0.8277 1.0000
0.000 0.2391 0.01747 0.00692 -0.0409 0.8108 1.0000
0.250 0.2618 0.01766 0.00698 -0.0397 0.7944 1.0000
0.500 0.2844 0.01785 0.00706 -0.0386 0.7787 1.0000
0.750 0.3069 0.01806 0.00717 -0.0374 0.7634 1.0000
1.000 0.3294 0.01828 0.00731 -0.0362 0.7486 1.0000
1.250 0.3520 0.01850 0.00746 -0.0351 0.7341 1.0000
1.500 0.3746 0.01873 0.00763 -0.0339 0.7197 1.0000
1.750 0.3973 0.01897 0.00783 -0.0327 0.7056 1.0000
2.000 0.4201 0.01922 0.00804 -0.0316 0.6915 1.0000
2.250 0.4429 0.01946 0.00828 -0.0304 0.6775 1.0000
2.500 0.4657 0.01971 0.00852 -0.0293 0.6635 1.0000
2.750 0.4890 0.01997 0.00877 -0.0282 0.6494 1.0000
3.000 0.5122 0.02023 0.00908 -0.0272 0.6353 1.0000
3.250 0.5353 0.02050 0.00936 -0.0261 0.6209 1.0000
3.500 0.5583 0.02077 0.00967 -0.0250 0.6063 1.0000
3.750 0.5813 0.02105 0.01000 -0.0238 0.5913 1.0000
4.000 0.6041 0.02134 0.01038 -0.0227 0.5760 1.0000
4.250 0.6268 0.02164 0.01075 -0.0216 0.5602 1.0000
4.500 0.6494 0.02193 0.01112 -0.0204 0.5440 1.0000
4.750 0.6719 0.02222 0.01148 -0.0192 0.5274 1.0000
5.000 0.6945 0.02250 0.01187 -0.0179 0.5105 1.0000
5.250 0.7170 0.02276 0.01220 -0.0166 0.4934 1.0000
5.500 0.7388 0.02311 0.01267 -0.0154 0.4742 1.0000
5.750 0.7605 0.02346 0.01312 -0.0141 0.4544 1.0000
6.000 0.7825 0.02375 0.01351 -0.0127 0.4349 1.0000
6.250 0.8030 0.02419 0.01409 -0.0113 0.4121 1.0000
6.500 0.8236 0.02458 0.01454 -0.0099 0.3895 1.0000
6.750 0.8434 0.02504 0.01511 -0.0085 0.3649 1.0000
7.000 0.8623 0.02560 0.01576 -0.0070 0.3388 1.0000
7.250 0.8803 0.02623 0.01650 -0.0055 0.3119 1.0000
7.500 0.8972 0.02697 0.01729 -0.0039 0.2841 1.0000
7.750 0.9128 0.02785 0.01818 -0.0023 0.2558 1.0000
8.000 0.9269 0.02889 0.01922 -0.0007 0.2280 1.0000
8.250 0.9392 0.03010 0.02041 0.0010 0.2008 1.0000
8.500 0.9498 0.03150 0.02178 0.0028 0.1757 1.0000
8.750 0.9581 0.03308 0.02329 0.0046 0.1529 1.0000
9.000 0.9641 0.03483 0.02508 0.0064 0.1293 1.0000
9.250 0.9674 0.03670 0.02689 0.0081 0.1100 1.0000
9.500 0.9696 0.03872 0.02892 0.0099 0.0934 1.0000
9.750 0.9699 0.04082 0.03103 0.0118 0.0822 1.0000
10.000 0.9686 0.04305 0.03316 0.0135 0.0743 1.0000
10.250 0.9729 0.04541 0.03577 0.0150 0.0668 1.0000
10.500 0.9751 0.04782 0.03810 0.0161 0.0622 1.0000
10.750 0.9807 0.05044 0.04106 0.0171 0.0572 1.0000
11.000 0.9830 0.05303 0.04377 0.0177 0.0536 1.0000
11.250 0.9861 0.05573 0.04646 0.0182 0.0507 1.0000
11.500 0.9871 0.05916 0.05027 0.0185 0.0485 1.0000
11.750 0.9859 0.06284 0.05429 0.0184 0.0471 1.0000
12.000 0.9804 0.06704 0.05876 0.0177 0.0460 1.0000
12.250 0.9716 0.07173 0.06368 0.0163 0.0454 1.0000
12.500 0.9593 0.07710 0.06928 0.0141 0.0451 1.0000
12.750 0.9429 0.08340 0.07580 0.0110 0.0451 1.0000
13.000 0.9217 0.09101 0.08360 0.0067 0.0452 1.0000
13.250 0.8960 0.10028 0.09301 0.0011 0.0459 1.0000
13.500 0.8666 0.11145 0.10428 -0.0057 0.0469 1.0000
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Polar data table (+)
Polar graphs
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