UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.55 at α=16.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ui1720-il-1000000.txt Download as CSV file: xf-ui1720-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.7449 0.09525 0.09301 -0.0155 1.0004 0.0157
-13.750 -0.7642 0.08794 0.08564 -0.0201 1.0004 0.0158
-13.500 -1.0263 0.03211 0.02896 -0.0757 1.0004 0.0137
-13.250 -1.0184 0.02718 0.02377 -0.0798 1.0004 0.0142
-13.000 -1.0010 0.02493 0.02138 -0.0808 1.0004 0.0146
-12.750 -0.9805 0.02338 0.01973 -0.0811 1.0004 0.0150
-12.500 -0.9586 0.02212 0.01837 -0.0812 1.0004 0.0155
-12.250 -0.9357 0.02105 0.01720 -0.0811 1.0004 0.0159
-12.000 -0.9126 0.01996 0.01600 -0.0809 1.0004 0.0164
-11.750 -0.8899 0.01868 0.01464 -0.0809 1.0004 0.0171
-11.500 -0.8657 0.01780 0.01371 -0.0806 1.0004 0.0178
-11.250 -0.8409 0.01708 0.01291 -0.0802 1.0004 0.0185
-11.000 -0.8158 0.01642 0.01217 -0.0797 1.0004 0.0192
-10.750 -0.6755 0.01496 0.01010 -0.1039 0.8008 0.0221
-10.500 -0.6619 0.01524 0.00947 -0.1013 0.5251 0.0233
-10.250 -0.6376 0.01502 0.00891 -0.1006 0.4314 0.0247
-10.000 -0.6122 0.01467 0.00833 -0.1001 0.3725 0.0263
-9.750 -0.5861 0.01435 0.00784 -0.0997 0.3354 0.0283
-9.500 -0.5596 0.01400 0.00738 -0.0993 0.3116 0.0305
-9.250 -0.5325 0.01373 0.00701 -0.0989 0.2977 0.0330
-9.000 -0.5050 0.01349 0.00674 -0.0986 0.2885 0.0357
-8.750 -0.4774 0.01333 0.00652 -0.0982 0.2814 0.0381
-8.500 -0.4495 0.01324 0.00636 -0.0978 0.2751 0.0405
-8.250 -0.4214 0.01312 0.00624 -0.0974 0.2725 0.0426
-8.000 -0.3930 0.01310 0.00617 -0.0971 0.2694 0.0446
-7.750 -0.3650 0.01302 0.00601 -0.0967 0.2665 0.0463
-7.500 -0.3369 0.01297 0.00594 -0.0963 0.2633 0.0478
-7.250 -0.3087 0.01299 0.00591 -0.0959 0.2601 0.0494
-7.000 -0.2802 0.01303 0.00587 -0.0955 0.2585 0.0508
-6.750 -0.2524 0.01277 0.00561 -0.0952 0.2578 0.0523
-6.500 -0.2241 0.01271 0.00553 -0.0948 0.2568 0.0536
-6.250 -0.1957 0.01266 0.00544 -0.0945 0.2558 0.0549
-6.000 -0.1673 0.01265 0.00536 -0.0941 0.2548 0.0562
-5.750 -0.1394 0.01241 0.00509 -0.0937 0.2538 0.0577
-5.500 -0.1112 0.01233 0.00502 -0.0934 0.2529 0.0591
-5.250 -0.0829 0.01229 0.00494 -0.0931 0.2520 0.0605
-5.000 -0.0546 0.01223 0.00483 -0.0927 0.2510 0.0617
-4.750 -0.0263 0.01220 0.00475 -0.0923 0.2502 0.0626
-4.500 0.0015 0.01191 0.00442 -0.0920 0.2493 0.0640
-4.250 0.0295 0.01177 0.00427 -0.0916 0.2483 0.0652
-4.000 0.0576 0.01170 0.00418 -0.0912 0.2471 0.0663
-3.750 0.0856 0.01167 0.00411 -0.0909 0.2460 0.0676
-3.500 0.1135 0.01165 0.00406 -0.0904 0.2449 0.0687
-3.250 0.1414 0.01166 0.00403 -0.0900 0.2439 0.0694
-3.000 0.1691 0.01159 0.00394 -0.0896 0.2431 0.0705
-2.750 0.1973 0.01144 0.00379 -0.0893 0.2429 0.0720
-2.500 0.2256 0.01137 0.00371 -0.0890 0.2427 0.0733
-2.250 0.2539 0.01132 0.00365 -0.0886 0.2425 0.0746
-2.000 0.2822 0.01129 0.00360 -0.0883 0.2422 0.0759
-1.750 0.3106 0.01129 0.00358 -0.0880 0.2420 0.0773
-1.500 0.3388 0.01122 0.00351 -0.0877 0.2417 0.0795
-1.250 0.3671 0.01120 0.00349 -0.0873 0.2414 0.0819
-1.000 0.3954 0.01121 0.00350 -0.0870 0.2411 0.0844
-0.750 0.4236 0.01122 0.00350 -0.0867 0.2409 0.0874
-0.500 0.4518 0.01122 0.00352 -0.0864 0.2406 0.0927
-0.250 0.4801 0.01123 0.00356 -0.0861 0.2403 0.1000
0.000 0.5082 0.01124 0.00361 -0.0858 0.2400 0.1123
0.250 0.5363 0.01124 0.00367 -0.0855 0.2397 0.1318
0.500 0.5644 0.01124 0.00376 -0.0852 0.2395 0.1610
0.750 0.5924 0.01124 0.00386 -0.0850 0.2392 0.1962
1.000 0.6204 0.01125 0.00397 -0.0847 0.2389 0.2349
1.500 0.6762 0.01127 0.00424 -0.0842 0.2385 0.3288
1.750 0.7041 0.01128 0.00440 -0.0840 0.2382 0.3897
2.000 0.7318 0.01129 0.00457 -0.0837 0.2380 0.4555
2.250 0.7594 0.01128 0.00475 -0.0834 0.2378 0.5321
2.500 0.7866 0.01124 0.00495 -0.0831 0.2376 0.6276
2.750 0.8121 0.01107 0.00517 -0.0823 0.2374 0.7721
3.000 0.8401 0.01083 0.00533 -0.0819 0.2372 0.9996
3.250 0.8680 0.01103 0.00550 -0.0816 0.2370 0.9996
3.500 0.8958 0.01123 0.00569 -0.0813 0.2368 0.9996
3.750 0.9236 0.01144 0.00588 -0.0811 0.2366 0.9996
4.000 0.9512 0.01166 0.00609 -0.0808 0.2365 0.9996
4.250 0.9789 0.01188 0.00630 -0.0805 0.2363 0.9996
4.500 1.0064 0.01211 0.00652 -0.0802 0.2361 0.9996
4.750 1.0340 0.01235 0.00675 -0.0799 0.2359 0.9996
5.000 1.0614 0.01256 0.00696 -0.0796 0.2356 0.9996
5.250 1.0889 0.01277 0.00716 -0.0793 0.2352 0.9996
5.500 1.1162 0.01300 0.00739 -0.0790 0.2350 0.9996
5.750 1.1434 0.01326 0.00765 -0.0787 0.2348 0.9996
6.000 1.1705 0.01351 0.00792 -0.0784 0.2345 0.9996
6.250 1.1976 0.01378 0.00819 -0.0781 0.2343 0.9996
6.500 1.2245 0.01406 0.00848 -0.0778 0.2341 0.9996
6.750 1.2514 0.01433 0.00877 -0.0775 0.2339 0.9996
7.000 1.2782 0.01462 0.00907 -0.0772 0.2337 0.9996
7.250 1.3050 0.01488 0.00934 -0.0769 0.2333 0.9996
7.500 1.3317 0.01511 0.00958 -0.0766 0.2329 0.9996
7.750 1.3583 0.01536 0.00984 -0.0763 0.2325 0.9996
8.000 1.3848 0.01566 0.01015 -0.0760 0.2321 0.9996
8.250 1.4110 0.01600 0.01052 -0.0757 0.2319 0.9996
8.500 1.4371 0.01636 0.01090 -0.0753 0.2316 0.9996
8.750 1.4630 0.01673 0.01130 -0.0750 0.2312 0.9996
9.000 1.4887 0.01715 0.01174 -0.0746 0.2307 0.9996
9.250 1.5139 0.01768 0.01231 -0.0743 0.2302 0.9996
9.500 1.5380 0.01846 0.01314 -0.0738 0.2295 0.9996
9.750 1.5586 0.01992 0.01472 -0.0731 0.2284 0.9996
10.000 1.5841 0.02016 0.01500 -0.0727 0.2283 0.9996
10.250 1.6095 0.02038 0.01527 -0.0723 0.2281 0.9996
10.500 1.6353 0.02045 0.01538 -0.0719 0.2278 0.9996
10.750 1.6610 0.02049 0.01546 -0.0715 0.2274 0.9996
11.000 1.6862 0.02063 0.01565 -0.0711 0.2270 0.9996
11.250 1.7110 0.02084 0.01591 -0.0706 0.2266 0.9996
11.500 1.7358 0.02102 0.01614 -0.0702 0.2261 0.9996
11.750 1.7607 0.02110 0.01626 -0.0697 0.2254 0.9996
12.000 1.7859 0.02103 0.01623 -0.0692 0.2244 0.9996
12.250 1.8104 0.02104 0.01630 -0.0687 0.2234 0.9996
12.500 1.8347 0.02116 0.01647 -0.0682 0.2226 0.9996
12.750 1.8600 0.02100 0.01632 -0.0677 0.2214 0.9996
13.000 1.8866 0.02053 0.01583 -0.0673 0.2199 0.9996
13.250 1.9128 0.02020 0.01547 -0.0670 0.2185 0.9996
13.500 1.9374 0.02013 0.01538 -0.0665 0.2168 0.9996
13.750 1.9580 0.02075 0.01605 -0.0657 0.2147 0.9996
14.000 1.9822 0.02046 0.01583 -0.0650 0.2139 0.9996
14.250 2.0060 0.02030 0.01575 -0.0644 0.2127 0.9996
14.500 2.0300 0.02014 0.01565 -0.0638 0.2111 0.9996
14.750 2.0542 0.01998 0.01554 -0.0632 0.2091 0.9996
15.000 2.0782 0.01987 0.01547 -0.0627 0.2073 0.9996
15.250 2.1020 0.01978 0.01541 -0.0621 0.2054 0.9996
15.500 2.1236 0.01983 0.01545 -0.0613 0.2028 0.9996
15.750 2.1471 0.01987 0.01560 -0.0608 0.2001 0.9996
16.000 2.1712 0.01988 0.01569 -0.0603 0.1950 0.9996
16.250 2.1945 0.01985 0.01564 -0.0598 0.1847 0.9996
16.500 2.1981 0.02096 0.01655 -0.0569 0.1619 0.9996
16.750 2.1906 0.02270 0.01826 -0.0527 0.1504 0.9996
17.000 2.1827 0.02451 0.02011 -0.0490 0.1415 0.9996
17.250 2.1688 0.02692 0.02256 -0.0455 0.1331 0.9996
17.500 2.1480 0.03034 0.02605 -0.0431 0.1255 0.9996
17.750 2.1222 0.03520 0.03104 -0.0429 0.1190 0.9996
18.000 2.0843 0.04310 0.03914 -0.0460 0.1167 0.9996
18.250 2.0297 0.05449 0.05083 -0.0513 0.1187 0.9996
18.500 1.9457 0.06921 0.06593 -0.0566 0.1265 0.9996
18.750 1.8535 0.08442 0.08146 -0.0616 0.1328 0.9996
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Polar data table (+)
Polar graphs
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