UAG 88-143/20 (uag8814320-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: UAG 88-143/20 (uag8814320-il) Reynolds number: 500,000 Max Cl/Cd: 126.97 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-uag8814320-il-500000.txt Download as CSV file: xf-uag8814320-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: UAG 88-143/20
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.1301 0.08739 0.08401 -0.1646 0.8347 0.0166
-10.500 0.1339 0.08494 0.08159 -0.1650 0.8335 0.0172
-10.250 0.1359 0.08223 0.07892 -0.1654 0.8321 0.0171
-10.000 0.1377 0.07958 0.07630 -0.1659 0.8307 0.0174
-9.750 0.0984 0.06904 0.06586 -0.1668 0.8286 0.0102
-9.500 0.0969 0.06639 0.06323 -0.1671 0.8270 0.0099
-9.250 0.0882 0.06294 0.05982 -0.1676 0.8252 0.0096
-9.000 0.0676 0.05816 0.05509 -0.1685 0.8231 0.0094
-8.750 -0.1519 0.02920 0.02534 -0.1623 0.8148 0.0072
-8.500 -0.1542 0.02608 0.02176 -0.1591 0.8128 0.0071
-8.250 -0.1469 0.02393 0.01923 -0.1566 0.8113 0.0071
-8.000 -0.1353 0.02217 0.01714 -0.1544 0.8101 0.0073
-7.750 -0.1186 0.02103 0.01575 -0.1529 0.8089 0.0074
-7.500 -0.1034 0.02020 0.01477 -0.1510 0.8068 0.0076
-7.250 -0.0861 0.01958 0.01404 -0.1494 0.8044 0.0081
-7.000 -0.0668 0.01892 0.01325 -0.1481 0.8025 0.0084
-6.750 -0.0455 0.01832 0.01251 -0.1470 0.8009 0.0090
-6.500 -0.0226 0.01775 0.01179 -0.1463 0.7996 0.0096
-6.250 0.0000 0.01703 0.01094 -0.1454 0.7983 0.0111
-6.000 0.0249 0.01662 0.01046 -0.1450 0.7972 0.0127
-5.750 0.0501 0.01623 0.00995 -0.1446 0.7962 0.0150
-5.500 0.0758 0.01598 0.00968 -0.1443 0.7953 0.0208
-5.250 0.0917 0.01599 0.00976 -0.1423 0.7919 0.0249
-5.000 0.1147 0.01600 0.00974 -0.1415 0.7895 0.0279
-4.750 0.1404 0.01602 0.00968 -0.1413 0.7879 0.0298
-4.500 0.1649 0.01564 0.00927 -0.1408 0.7865 0.0332
-4.250 0.1924 0.01551 0.00913 -0.1409 0.7853 0.0368
-4.000 0.2210 0.01547 0.00903 -0.1412 0.7842 0.0403
-3.750 0.2468 0.01507 0.00861 -0.1409 0.7833 0.0455
-3.500 0.2753 0.01497 0.00846 -0.1412 0.7825 0.0507
-3.250 0.2938 0.01518 0.00866 -0.1396 0.7794 0.0536
-3.000 0.3114 0.01503 0.00856 -0.1379 0.7761 0.0606
-2.750 0.3368 0.01489 0.00838 -0.1375 0.7744 0.0651
-2.500 0.3629 0.01462 0.00808 -0.1373 0.7729 0.0702
-2.250 0.3905 0.01436 0.00781 -0.1373 0.7718 0.0770
-2.000 0.4187 0.01410 0.00754 -0.1375 0.7708 0.0856
-1.750 0.4473 0.01382 0.00729 -0.1378 0.7699 0.1015
-1.500 0.4752 0.01345 0.00707 -0.1381 0.7691 0.1499
-1.250 0.4830 0.01350 0.00741 -0.1345 0.7641 0.2267
-1.000 0.5011 0.01297 0.00736 -0.1330 0.7616 0.3832
-0.750 0.5136 0.01207 0.00727 -0.1300 0.7597 0.6498
-0.500 0.5518 0.01139 0.00733 -0.1319 0.7589 0.9068
-0.250 0.6326 0.01142 0.00731 -0.1433 0.7589 0.9576
0.000 0.6850 0.01140 0.00721 -0.1486 0.7583 0.9742
0.250 0.7344 0.01131 0.00705 -0.1533 0.7575 0.9835
0.500 0.8164 0.01121 0.00688 -0.1651 0.7573 0.9956
0.750 0.8696 0.01102 0.00663 -0.1708 0.7566 1.0000
1.000 0.8952 0.01089 0.00645 -0.1707 0.7551 1.0000
1.250 0.8996 0.01113 0.00674 -0.1663 0.7497 1.0000
1.500 0.9227 0.01100 0.00659 -0.1655 0.7473 1.0000
1.750 0.9491 0.01080 0.00636 -0.1654 0.7455 1.0000
2.000 0.9774 0.01058 0.00610 -0.1657 0.7439 1.0000
2.250 1.0079 0.01038 0.00585 -0.1664 0.7425 1.0000
2.500 1.0125 0.01060 0.00615 -0.1619 0.7370 1.0000
2.750 1.0350 0.01049 0.00603 -0.1610 0.7340 1.0000
3.000 1.0629 0.01029 0.00581 -0.1612 0.7317 1.0000
3.250 1.0942 0.01007 0.00557 -0.1620 0.7297 1.0000
3.500 1.1020 0.01021 0.00576 -0.1581 0.7242 1.0000
3.750 1.1244 0.01010 0.00565 -0.1571 0.7203 1.0000
4.000 1.1536 0.00991 0.00545 -0.1575 0.7173 1.0000
4.250 1.1675 0.00998 0.00556 -0.1548 0.7123 1.0000
4.500 1.1858 0.00996 0.00556 -0.1530 0.7073 1.0000
4.750 1.2142 0.00982 0.00541 -0.1533 0.7035 1.0000
5.000 1.2230 0.00996 0.00559 -0.1496 0.6970 1.0000
5.250 1.2438 0.00992 0.00556 -0.1483 0.6915 1.0000
5.500 1.2587 0.01000 0.00567 -0.1458 0.6852 1.0000
5.750 1.2733 0.01005 0.00574 -0.1432 0.6783 1.0000
6.000 1.2810 0.01016 0.00587 -0.1392 0.6706 1.0000
6.250 1.2964 0.01021 0.00591 -0.1367 0.6632 1.0000
6.500 1.2970 0.01045 0.00618 -0.1314 0.6538 1.0000
6.750 1.3089 0.01063 0.00636 -0.1284 0.6447 1.0000
7.000 1.3202 0.01085 0.00656 -0.1254 0.6340 1.0000
7.250 1.3226 0.01128 0.00700 -0.1209 0.6194 1.0000
7.500 1.3159 0.01207 0.00770 -0.1150 0.5949 1.0000
7.750 1.3174 0.01287 0.00845 -0.1109 0.5743 1.0000
8.000 1.3148 0.01394 0.00940 -0.1063 0.5476 1.0000
8.250 1.3106 0.01518 0.01050 -0.1016 0.5180 1.0000
8.500 1.3085 0.01642 0.01161 -0.0975 0.4911 1.0000
8.750 1.2991 0.01806 0.01306 -0.0924 0.4547 1.0000
9.000 1.2915 0.01971 0.01452 -0.0878 0.4188 1.0000
9.250 1.2786 0.02176 0.01631 -0.0827 0.3736 1.0000
9.500 1.2699 0.02375 0.01805 -0.0784 0.3310 1.0000
9.750 1.2646 0.02565 0.01973 -0.0747 0.2906 1.0000
10.000 1.2507 0.02817 0.02186 -0.0702 0.2310 1.0000
10.250 1.2339 0.03101 0.02424 -0.0656 0.1605 1.0000
10.500 1.2185 0.03390 0.02667 -0.0614 0.0927 1.0000
10.750 1.1969 0.03742 0.02970 -0.0568 0.0214 1.0000
11.000 1.1982 0.03939 0.03162 -0.0546 0.0082 1.0000
11.250 1.2079 0.04074 0.03304 -0.0532 0.0073 1.0000
11.500 1.2141 0.04242 0.03482 -0.0516 0.0062 1.0000
11.750 1.2185 0.04427 0.03680 -0.0498 0.0057 1.0000
12.000 1.2256 0.04592 0.03855 -0.0484 0.0056 1.0000
12.250 1.2317 0.04770 0.04041 -0.0470 0.0054 1.0000
12.500 1.2359 0.04968 0.04249 -0.0456 0.0053 1.0000
12.750 1.2403 0.05169 0.04460 -0.0443 0.0053 1.0000
13.000 1.2426 0.05393 0.04693 -0.0428 0.0052 1.0000
13.250 1.2430 0.05641 0.04953 -0.0414 0.0052 1.0000
13.500 1.2454 0.05873 0.05194 -0.0402 0.0052 1.0000
13.750 1.2442 0.06146 0.05478 -0.0389 0.0051 1.0000
14.000 1.2435 0.06420 0.05761 -0.0377 0.0051 1.0000
14.250 1.2433 0.06688 0.06039 -0.0366 0.0051 1.0000
14.500 1.2416 0.06974 0.06334 -0.0354 0.0052 1.0000
14.750 1.2422 0.07237 0.06607 -0.0344 0.0052 1.0000
15.000 1.2420 0.07506 0.06885 -0.0333 0.0052 1.0000
15.250 1.2433 0.07752 0.07139 -0.0322 0.0053 1.0000
15.500 1.2463 0.07975 0.07370 -0.0311 0.0054 1.0000
15.750 1.2508 0.08174 0.07577 -0.0299 0.0054 1.0000
16.000 1.2559 0.08380 0.07794 -0.0290 0.0054 1.0000
16.250 1.2625 0.08550 0.07972 -0.0277 0.0054 1.0000
16.500 1.2644 0.08836 0.08270 -0.0277 0.0052 1.0000
16.750 1.2649 0.09157 0.08605 -0.0283 0.0048 1.0000
17.000 1.2692 0.09358 0.08819 -0.0269 0.0050 1.0000
17.250 1.2711 0.09614 0.09091 -0.0261 0.0051 1.0000
17.500 1.2715 0.09898 0.09390 -0.0254 0.0052 1.0000
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