UAG 88-143/20 (uag8814320-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: UAG 88-143/20 (uag8814320-il) Reynolds number: 100,000 Max Cl/Cd: 30.31 at α=11° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-uag8814320-il-100000-n5.txt Download as CSV file: xf-uag8814320-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 0.0690 0.11196 0.10598 -0.1488 0.8872 0.0211
-11.750 0.0735 0.10947 0.10351 -0.1491 0.8855 0.0200
-11.500 0.0766 0.10690 0.10094 -0.1495 0.8838 0.0196
-11.250 0.0791 0.10414 0.09822 -0.1500 0.8820 0.0187
-11.000 0.0809 0.10122 0.09531 -0.1507 0.8801 0.0179
-10.500 0.0791 0.09408 0.08821 -0.1533 0.8763 0.0161
-10.250 0.0801 0.09138 0.08555 -0.1537 0.8746 0.0161
-10.000 0.0811 0.08988 0.08409 -0.1528 0.8722 0.0158
-9.750 0.0768 0.08730 0.08158 -0.1524 0.8694 0.0159
-9.500 0.0765 0.08509 0.07940 -0.1522 0.8667 0.0157
-9.250 0.0751 0.08244 0.07679 -0.1524 0.8644 0.0156
-9.000 0.0738 0.07971 0.07409 -0.1529 0.8624 0.0154
-8.750 0.0649 0.07812 0.07257 -0.1512 0.8589 0.0152
-8.500 0.0529 0.07647 0.07101 -0.1492 0.8545 0.0151
-8.250 0.0432 0.07419 0.06878 -0.1485 0.8513 0.0150
-8.000 0.0321 0.07123 0.06586 -0.1487 0.8483 0.0150
-7.750 -0.0024 0.07211 0.06687 -0.1413 0.8409 0.0148
-7.500 -0.0176 0.06988 0.06466 -0.1400 0.8370 0.0146
-7.250 -0.0383 0.06884 0.06365 -0.1360 0.8316 0.0143
-7.000 -0.0646 0.06765 0.06250 -0.1309 0.8253 0.0144
-6.750 -0.0689 0.06367 0.05841 -0.1311 0.8224 0.0142
-6.500 -0.1102 0.06523 0.06008 -0.1202 0.8132 0.0141
-6.250 -0.1131 0.06066 0.05533 -0.1199 0.8100 0.0141
-6.000 -0.1379 0.06001 0.05466 -0.1129 0.8027 0.0139
-5.750 -0.1429 0.05584 0.05025 -0.1107 0.7985 0.0138
-5.500 -0.1369 0.04942 0.04331 -0.1102 0.7961 0.0137
-5.250 -0.1431 0.04612 0.03958 -0.1060 0.7912 0.0136
-5.000 -0.1414 0.04279 0.03568 -0.1026 0.7868 0.0140
-4.750 -0.1235 0.03968 0.03191 -0.1013 0.7845 0.0144
-4.500 -0.0995 0.03729 0.02887 -0.1006 0.7830 0.0161
-4.250 -0.0722 0.03628 0.02763 -0.1007 0.7817 0.0176
-4.000 -0.0739 0.03671 0.02801 -0.0963 0.7753 0.0205
-3.750 -0.0527 0.03631 0.02745 -0.0954 0.7723 0.0256
-3.250 0.0019 0.03527 0.02588 -0.0951 0.7689 0.0426
-3.000 0.0081 0.03568 0.02627 -0.0921 0.7633 0.0482
-2.750 0.0276 0.03562 0.02596 -0.0909 0.7597 0.0553
-2.500 0.0526 0.03535 0.02566 -0.0907 0.7575 0.0628
-2.250 0.0813 0.03500 0.02509 -0.0907 0.7559 0.0689
-2.000 0.0902 0.03514 0.02525 -0.0882 0.7506 0.0744
-1.750 0.1085 0.03523 0.02522 -0.0868 0.7467 0.0833
-1.500 0.1337 0.03497 0.02494 -0.0866 0.7443 0.0928
-1.250 0.1619 0.03464 0.02455 -0.0866 0.7427 0.1021
-1.000 0.1690 0.03499 0.02486 -0.0837 0.7366 0.1084
-0.750 0.1898 0.03494 0.02480 -0.0828 0.7329 0.1228
-0.500 0.2175 0.03468 0.02459 -0.0829 0.7308 0.1464
-0.250 0.2479 0.03429 0.02439 -0.0835 0.7292 0.2105
0.000 0.3328 0.03286 0.02515 -0.0958 0.7294 1.0000
0.500 0.3600 0.03379 0.02571 -0.0919 0.7188 1.0000
0.750 0.3885 0.03385 0.02558 -0.0921 0.7167 1.0000
1.000 0.4185 0.03387 0.02542 -0.0924 0.7150 1.0000
1.250 0.4188 0.03478 0.02625 -0.0888 0.7060 1.0000
1.500 0.4470 0.03483 0.02615 -0.0889 0.7037 1.0000
1.750 0.4777 0.03481 0.02600 -0.0894 0.7021 1.0000
2.000 0.4794 0.03576 0.02689 -0.0861 0.6928 1.0000
2.250 0.5077 0.03579 0.02681 -0.0862 0.6904 1.0000
2.500 0.5382 0.03573 0.02665 -0.0867 0.6887 1.0000
2.750 0.5411 0.03672 0.02761 -0.0836 0.6793 1.0000
3.000 0.5697 0.03670 0.02751 -0.0838 0.6768 1.0000
3.250 0.6005 0.03657 0.02732 -0.0842 0.6750 1.0000
3.500 0.6044 0.03759 0.02832 -0.0814 0.6653 1.0000
3.750 0.6331 0.03753 0.02821 -0.0816 0.6627 1.0000
4.000 0.6646 0.03730 0.02795 -0.0821 0.6610 1.0000
4.250 0.6680 0.03843 0.02910 -0.0793 0.6508 1.0000
4.500 0.6981 0.03821 0.02885 -0.0796 0.6485 1.0000
5.000 0.7332 0.03909 0.02974 -0.0774 0.6361 1.0000
5.250 0.7643 0.03874 0.02941 -0.0777 0.6340 1.0000
5.500 0.7705 0.03984 0.03054 -0.0755 0.6238 1.0000
5.750 0.8001 0.03952 0.03025 -0.0756 0.6212 1.0000
6.000 0.8318 0.03905 0.02983 -0.0759 0.6194 1.0000
6.250 0.8372 0.04021 0.03103 -0.0736 0.6084 1.0000
6.500 0.8682 0.03969 0.03057 -0.0738 0.6062 1.0000
6.750 0.8757 0.04076 0.03170 -0.0718 0.5956 1.0000
7.000 0.9055 0.04024 0.03124 -0.0718 0.5929 1.0000
7.500 0.9444 0.04065 0.03182 -0.0699 0.5795 1.0000
7.750 0.9766 0.03991 0.03116 -0.0701 0.5772 1.0000
8.000 0.9843 0.04099 0.03233 -0.0682 0.5660 1.0000
8.250 1.0180 0.04010 0.03155 -0.0684 0.5634 1.0000
9.250 1.0863 0.04160 0.03350 -0.0639 0.5274 1.0000
9.500 1.1193 0.04066 0.03269 -0.0640 0.5219 1.0000
10.000 1.1540 0.04143 0.03373 -0.0618 0.5006 1.0000
10.250 1.1883 0.04038 0.03281 -0.0620 0.4924 1.0000
10.500 1.2048 0.04082 0.03337 -0.0608 0.4795 1.0000
10.750 1.2236 0.04107 0.03374 -0.0598 0.4660 1.0000
11.000 1.2449 0.04107 0.03384 -0.0589 0.4506 1.0000
11.250 1.2578 0.04173 0.03460 -0.0573 0.4319 1.0000
11.500 1.2655 0.04260 0.03541 -0.0551 0.4036 1.0000
11.750 1.2652 0.04411 0.03672 -0.0524 0.3657 1.0000
12.000 1.2614 0.04616 0.03858 -0.0497 0.3272 1.0000
12.250 1.2569 0.04844 0.04065 -0.0472 0.2896 1.0000
12.500 1.2505 0.05107 0.04306 -0.0448 0.2522 1.0000
12.750 1.2430 0.05397 0.04576 -0.0427 0.2139 1.0000
13.000 1.2349 0.05707 0.04864 -0.0408 0.1766 1.0000
13.250 1.2160 0.06140 0.05249 -0.0386 0.1205 1.0000
13.500 1.2037 0.06523 0.05598 -0.0370 0.0790 1.0000
13.750 1.1902 0.06935 0.05976 -0.0355 0.0405 1.0000
14.000 1.1801 0.07327 0.06351 -0.0343 0.0209 1.0000
14.250 1.1764 0.07662 0.06690 -0.0335 0.0163 1.0000
14.500 1.1739 0.07992 0.07034 -0.0329 0.0142 1.0000
14.750 1.1712 0.08332 0.07392 -0.0324 0.0130 1.0000
15.000 1.1663 0.08708 0.07784 -0.0321 0.0121 1.0000
15.250 1.1642 0.09055 0.08147 -0.0320 0.0119 1.0000
15.500 1.1598 0.09441 0.08555 -0.0320 0.0112 1.0000
15.750 1.1568 0.09813 0.08945 -0.0322 0.0109 1.0000
16.000 1.1530 0.10203 0.09354 -0.0325 0.0106 1.0000
16.250 1.1491 0.10598 0.09766 -0.0330 0.0101 1.0000
16.500 1.1462 0.10981 0.10165 -0.0336 0.0098 1.0000
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