UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Reynolds number: 500,000 Max Cl/Cd: 78.05 at α=15° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ui1720-il-500000-n5.txt Download as CSV file: xf-ui1720-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: UNIVERSITY OF ILLINOIS UI-1720 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 -0.5603 0.10331 0.09888 -0.0202 0.4192 0.0177
-12.750 -0.5853 0.09434 0.08992 -0.0255 0.4353 0.0184
-12.250 -0.9046 0.03028 0.02651 -0.0753 1.0004 0.0159
-12.000 -0.8882 0.02744 0.02346 -0.0770 1.0004 0.0164
-11.750 -0.8693 0.02527 0.02114 -0.0780 1.0004 0.0169
-11.250 -0.7311 0.02153 0.01616 -0.0990 0.6779 0.0197
-11.000 -0.7130 0.02120 0.01512 -0.0980 0.4878 0.0206
-10.750 -0.6893 0.02055 0.01415 -0.0978 0.4204 0.0217
-10.500 -0.6648 0.01984 0.01320 -0.0976 0.3770 0.0228
-10.250 -0.6396 0.01920 0.01236 -0.0975 0.3481 0.0242
-10.000 -0.6138 0.01862 0.01161 -0.0972 0.3277 0.0256
-9.500 -0.5614 0.01756 0.01030 -0.0968 0.3019 0.0291
-9.250 -0.5347 0.01714 0.00979 -0.0965 0.2929 0.0312
-9.000 -0.5077 0.01677 0.00933 -0.0962 0.2867 0.0334
-8.750 -0.4804 0.01648 0.00896 -0.0959 0.2810 0.0357
-8.250 -0.4254 0.01603 0.00835 -0.0953 0.2728 0.0400
-8.000 -0.3977 0.01584 0.00808 -0.0949 0.2697 0.0419
-7.750 -0.3698 0.01569 0.00786 -0.0946 0.2668 0.0438
-7.500 -0.3421 0.01549 0.00752 -0.0942 0.2641 0.0457
-7.250 -0.3143 0.01536 0.00735 -0.0938 0.2616 0.0471
-6.750 -0.2585 0.01512 0.00692 -0.0931 0.2580 0.0505
-6.500 -0.2306 0.01494 0.00671 -0.0928 0.2568 0.0519
-6.250 -0.2025 0.01484 0.00657 -0.0924 0.2555 0.0533
-6.000 -0.1745 0.01472 0.00638 -0.0921 0.2543 0.0549
-5.750 -0.1464 0.01459 0.00615 -0.0917 0.2530 0.0563
-5.500 -0.1186 0.01438 0.00591 -0.0914 0.2519 0.0575
-5.250 -0.0907 0.01425 0.00574 -0.0910 0.2508 0.0588
-5.000 -0.0627 0.01413 0.00557 -0.0907 0.2497 0.0601
-4.750 -0.0347 0.01401 0.00538 -0.0903 0.2487 0.0614
-4.500 -0.0066 0.01390 0.00518 -0.0900 0.2478 0.0625
-4.250 0.0212 0.01372 0.00497 -0.0896 0.2469 0.0636
-4.000 0.0491 0.01359 0.00481 -0.0893 0.2459 0.0648
-3.750 0.0770 0.01350 0.00468 -0.0889 0.2451 0.0659
-3.500 0.1049 0.01344 0.00457 -0.0885 0.2442 0.0671
-3.250 0.1328 0.01339 0.00447 -0.0881 0.2433 0.0683
-3.000 0.1609 0.01331 0.00435 -0.0878 0.2429 0.0693
-2.750 0.1891 0.01321 0.00423 -0.0875 0.2426 0.0704
-2.500 0.2172 0.01311 0.00413 -0.0871 0.2422 0.0720
-2.250 0.2454 0.01305 0.00406 -0.0868 0.2417 0.0735
-2.000 0.2736 0.01300 0.00399 -0.0865 0.2412 0.0751
-1.750 0.3018 0.01297 0.00394 -0.0862 0.2407 0.0768
-1.500 0.3300 0.01294 0.00389 -0.0859 0.2402 0.0786
-1.250 0.3581 0.01291 0.00387 -0.0855 0.2398 0.0811
-1.000 0.3863 0.01292 0.00387 -0.0852 0.2394 0.0843
-0.750 0.4144 0.01292 0.00387 -0.0849 0.2390 0.0880
-0.500 0.4425 0.01293 0.00389 -0.0846 0.2386 0.0929
-0.250 0.4706 0.01295 0.00392 -0.0843 0.2381 0.0991
0.000 0.4986 0.01298 0.00397 -0.0840 0.2377 0.1076
0.500 0.5546 0.01302 0.00410 -0.0834 0.2370 0.1356
0.750 0.5826 0.01304 0.00418 -0.0831 0.2366 0.1589
1.000 0.6105 0.01306 0.00428 -0.0828 0.2362 0.1872
1.250 0.6383 0.01309 0.00439 -0.0826 0.2359 0.2189
1.500 0.6662 0.01313 0.00452 -0.0823 0.2355 0.2545
1.750 0.6939 0.01316 0.00465 -0.0821 0.2352 0.2967
2.000 0.7216 0.01318 0.00481 -0.0818 0.2349 0.3475
2.250 0.7493 0.01319 0.00498 -0.0816 0.2346 0.4070
2.500 0.7767 0.01320 0.00516 -0.0813 0.2343 0.4765
2.750 0.8036 0.01311 0.00538 -0.0810 0.2340 0.5906
3.000 0.8281 0.01287 0.00560 -0.0800 0.2338 0.7546
3.250 0.8560 0.01262 0.00573 -0.0795 0.2335 0.9996
3.500 0.8837 0.01283 0.00591 -0.0792 0.2332 0.9996
3.750 0.9113 0.01305 0.00609 -0.0789 0.2330 0.9996
4.000 0.9388 0.01327 0.00629 -0.0786 0.2327 0.9996
4.500 0.9936 0.01374 0.00672 -0.0780 0.2322 0.9996
4.750 1.0208 0.01399 0.00695 -0.0777 0.2320 0.9996
5.000 1.0480 0.01424 0.00719 -0.0773 0.2318 0.9996
5.250 1.0751 0.01450 0.00745 -0.0770 0.2316 0.9996
5.500 1.1022 0.01478 0.00772 -0.0767 0.2313 0.9996
5.750 1.1291 0.01506 0.00800 -0.0764 0.2311 0.9996
6.000 1.1559 0.01535 0.00830 -0.0761 0.2309 0.9996
6.250 1.1827 0.01566 0.00861 -0.0757 0.2307 0.9996
6.500 1.2093 0.01598 0.00894 -0.0754 0.2304 0.9996
6.750 1.2358 0.01632 0.00929 -0.0751 0.2301 0.9996
7.000 1.2621 0.01668 0.00966 -0.0747 0.2297 0.9996
7.250 1.2883 0.01708 0.01008 -0.0744 0.2293 0.9996
7.500 1.3142 0.01752 0.01054 -0.0740 0.2290 0.9996
7.750 1.3400 0.01800 0.01105 -0.0737 0.2287 0.9996
8.000 1.3656 0.01845 0.01154 -0.0733 0.2284 0.9996
8.250 1.3914 0.01881 0.01194 -0.0729 0.2283 0.9996
8.500 1.4170 0.01916 0.01234 -0.0725 0.2282 0.9996
8.750 1.4425 0.01947 0.01271 -0.0721 0.2279 0.9996
9.000 1.4678 0.01976 0.01306 -0.0716 0.2276 0.9996
9.250 1.4929 0.02009 0.01345 -0.0712 0.2273 0.9996
9.500 1.5177 0.02048 0.01390 -0.0707 0.2271 0.9996
9.750 1.5423 0.02089 0.01439 -0.0703 0.2268 0.9996
10.000 1.5666 0.02130 0.01487 -0.0698 0.2265 0.9996
10.250 1.5908 0.02168 0.01533 -0.0692 0.2260 0.9996
10.500 1.6147 0.02202 0.01575 -0.0687 0.2254 0.9996
10.750 1.6383 0.02240 0.01621 -0.0681 0.2248 0.9996
11.000 1.6616 0.02283 0.01672 -0.0675 0.2243 0.9996
11.250 1.6847 0.02329 0.01726 -0.0669 0.2239 0.9996
11.500 1.7074 0.02374 0.01780 -0.0662 0.2233 0.9996
11.750 1.7302 0.02410 0.01824 -0.0656 0.2226 0.9996
12.000 1.7531 0.02437 0.01857 -0.0649 0.2217 0.9996
12.250 1.7760 0.02460 0.01887 -0.0642 0.2208 0.9996
12.500 1.7985 0.02490 0.01923 -0.0635 0.2200 0.9996
12.750 1.8213 0.02509 0.01948 -0.0629 0.2192 0.9996
13.000 1.8446 0.02515 0.01957 -0.0622 0.2181 0.9996
13.250 1.8679 0.02519 0.01962 -0.0616 0.2171 0.9996
13.500 1.8901 0.02534 0.01978 -0.0608 0.2158 0.9996
13.750 1.9099 0.02563 0.02014 -0.0598 0.2143 0.9996
14.000 1.9282 0.02581 0.02048 -0.0586 0.2127 0.9996
14.250 1.9468 0.02602 0.02083 -0.0574 0.2108 0.9996
14.500 1.9667 0.02600 0.02090 -0.0563 0.2081 0.9996
14.750 1.9879 0.02579 0.02072 -0.0553 0.2052 0.9996
15.000 2.0066 0.02571 0.02066 -0.0540 0.2029 0.9996
15.250 2.0209 0.02622 0.02131 -0.0524 0.2003 0.9996
15.500 2.0345 0.02679 0.02206 -0.0508 0.1965 0.9996
15.750 2.0503 0.02703 0.02237 -0.0493 0.1917 0.9996
16.000 2.0637 0.02753 0.02296 -0.0478 0.1855 0.9996
16.500 2.0620 0.03022 0.02546 -0.0437 0.1575 0.9996
16.750 2.0414 0.03402 0.02934 -0.0424 0.1503 0.9996
17.000 2.0126 0.03988 0.03535 -0.0437 0.1460 0.9996
17.250 1.9697 0.04913 0.04487 -0.0481 0.1443 0.9996
17.500 1.8873 0.06431 0.06045 -0.0547 0.1487 0.9996
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