UAG 88-143/20 (uag8814320-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: UAG 88-143/20 (uag8814320-il) Reynolds number: 500,000 Max Cl/Cd: 123.92 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-uag8814320-il-500000-n5.txt Download as CSV file: xf-uag8814320-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.1002 0.08709 0.08342 -0.1572 0.8025 0.0052
-10.750 0.1016 0.08374 0.08010 -0.1582 0.8015 0.0051
-10.500 0.1027 0.08042 0.07680 -0.1591 0.8004 0.0049
-10.250 0.0992 0.07635 0.07275 -0.1601 0.7992 0.0047
-10.000 0.0970 0.07265 0.06908 -0.1612 0.7982 0.0045
-9.750 0.0419 0.06107 0.05759 -0.1634 0.7965 0.0040
-9.500 0.0213 0.05575 0.05229 -0.1653 0.7951 0.0040
-9.250 -0.0132 0.05010 0.04673 -0.1673 0.7929 0.0039
-8.750 -0.1163 0.02975 0.02578 -0.1644 0.7874 0.0038
-8.500 -0.1187 0.02616 0.02177 -0.1619 0.7858 0.0038
-8.250 -0.1111 0.02386 0.01914 -0.1598 0.7845 0.0038
-8.000 -0.0996 0.02195 0.01690 -0.1579 0.7834 0.0037
-7.750 -0.0835 0.02057 0.01526 -0.1566 0.7825 0.0037
-7.500 -0.0654 0.01938 0.01382 -0.1554 0.7816 0.0037
-7.250 -0.0460 0.01846 0.01272 -0.1542 0.7805 0.0037
-7.000 -0.0275 0.01755 0.01164 -0.1528 0.7788 0.0037
-6.750 -0.0069 0.01683 0.01078 -0.1518 0.7772 0.0037
-6.500 0.0146 0.01618 0.01000 -0.1508 0.7758 0.0037
-6.250 0.0371 0.01558 0.00929 -0.1500 0.7744 0.0036
-6.000 0.0605 0.01507 0.00865 -0.1494 0.7731 0.0036
-5.750 0.0847 0.01458 0.00805 -0.1489 0.7718 0.0037
-5.500 0.1095 0.01414 0.00751 -0.1484 0.7708 0.0037
-5.250 0.1349 0.01376 0.00703 -0.1481 0.7698 0.0037
-5.000 0.1607 0.01339 0.00655 -0.1479 0.7688 0.0037
-4.750 0.1869 0.01307 0.00615 -0.1477 0.7679 0.0037
-4.500 0.2099 0.01284 0.00586 -0.1469 0.7661 0.0037
-4.250 0.2335 0.01264 0.00562 -0.1462 0.7643 0.0037
-4.000 0.2577 0.01242 0.00535 -0.1456 0.7625 0.0038
-3.750 0.2827 0.01221 0.00509 -0.1452 0.7609 0.0039
-3.500 0.3083 0.01201 0.00484 -0.1448 0.7594 0.0039
-3.250 0.3344 0.01182 0.00460 -0.1446 0.7581 0.0041
-3.000 0.3611 0.01164 0.00438 -0.1445 0.7569 0.0044
-2.750 0.3881 0.01147 0.00418 -0.1445 0.7557 0.0051
-2.250 0.4361 0.01112 0.00396 -0.1434 0.7522 0.0312
-2.000 0.4597 0.01103 0.00393 -0.1427 0.7499 0.0426
-1.750 0.4842 0.01088 0.00387 -0.1423 0.7479 0.0597
-1.500 0.5098 0.01075 0.00378 -0.1420 0.7460 0.0727
-1.250 0.5362 0.01061 0.00366 -0.1419 0.7444 0.0861
-1.000 0.5628 0.01043 0.00354 -0.1418 0.7429 0.1132
-0.750 0.5882 0.01013 0.00345 -0.1417 0.7414 0.1873
-0.500 0.6049 0.00981 0.00355 -0.1398 0.7381 0.3134
-0.250 0.6242 0.00948 0.00356 -0.1384 0.7353 0.4380
0.000 0.6430 0.00909 0.00355 -0.1368 0.7328 0.5743
0.250 0.6592 0.00862 0.00353 -0.1345 0.7306 0.7265
0.500 0.6976 0.00825 0.00362 -0.1366 0.7291 0.9019
0.750 0.7903 0.00838 0.00376 -0.1509 0.7282 0.9716
1.000 0.8317 0.00852 0.00390 -0.1542 0.7249 0.9840
1.250 0.8775 0.00857 0.00393 -0.1585 0.7219 0.9909
1.500 0.9175 0.00858 0.00391 -0.1615 0.7190 0.9957
1.750 0.9547 0.00854 0.00383 -0.1639 0.7163 0.9985
2.000 0.9828 0.00858 0.00387 -0.1643 0.7124 1.0000
2.250 1.0001 0.00863 0.00392 -0.1624 0.7077 1.0000
2.500 1.0207 0.00863 0.00389 -0.1611 0.7038 1.0000
2.750 1.0394 0.00868 0.00394 -0.1595 0.6994 1.0000
3.000 1.0557 0.00875 0.00402 -0.1573 0.6940 1.0000
3.250 1.0757 0.00878 0.00401 -0.1559 0.6892 1.0000
3.500 1.0909 0.00888 0.00414 -0.1535 0.6834 1.0000
3.750 1.1074 0.00896 0.00420 -0.1513 0.6772 1.0000
4.000 1.1224 0.00906 0.00430 -0.1489 0.6707 1.0000
4.250 1.1363 0.00917 0.00441 -0.1462 0.6637 1.0000
4.500 1.1472 0.00930 0.00453 -0.1429 0.6563 1.0000
4.750 1.1557 0.00943 0.00464 -0.1390 0.6486 1.0000
5.000 1.1637 0.00961 0.00482 -0.1351 0.6403 1.0000
5.250 1.1739 0.00981 0.00500 -0.1318 0.6316 1.0000
5.500 1.1831 0.01007 0.00527 -0.1283 0.6219 1.0000
5.750 1.1925 0.01039 0.00558 -0.1250 0.6116 1.0000
6.000 1.2017 0.01078 0.00594 -0.1218 0.6005 1.0000
6.250 1.2101 0.01125 0.00639 -0.1186 0.5882 1.0000
6.500 1.2176 0.01184 0.00694 -0.1154 0.5739 1.0000
6.750 1.2264 0.01245 0.00755 -0.1126 0.5605 1.0000
7.000 1.2342 0.01317 0.00822 -0.1097 0.5449 1.0000
7.250 1.2410 0.01396 0.00897 -0.1067 0.5277 1.0000
7.500 1.2485 0.01477 0.00973 -0.1039 0.5114 1.0000
7.750 1.2494 0.01588 0.01073 -0.1001 0.4875 1.0000
8.000 1.2518 0.01698 0.01174 -0.0967 0.4652 1.0000
8.250 1.2493 0.01835 0.01297 -0.0927 0.4361 1.0000
8.500 1.2507 0.01960 0.01412 -0.0894 0.4097 1.0000
8.750 1.2437 0.02134 0.01565 -0.0851 0.3714 1.0000
9.000 1.2386 0.02309 0.01719 -0.0812 0.3341 1.0000
9.250 1.2299 0.02516 0.01896 -0.0770 0.2844 1.0000
9.500 1.2264 0.02701 0.02056 -0.0737 0.2425 1.0000
9.750 1.2263 0.02873 0.02208 -0.0708 0.2064 1.0000
10.000 1.2261 0.03049 0.02362 -0.0681 0.1691 1.0000
10.250 1.2206 0.03267 0.02552 -0.0649 0.1213 1.0000
10.500 1.2194 0.03465 0.02728 -0.0623 0.0845 1.0000
10.750 1.2142 0.03697 0.02936 -0.0593 0.0461 1.0000
11.250 1.2133 0.04118 0.03337 -0.0547 0.0048 1.0000
11.500 1.2221 0.04263 0.03488 -0.0534 0.0037 1.0000
11.750 1.2303 0.04414 0.03647 -0.0521 0.0031 1.0000
12.000 1.2399 0.04557 0.03798 -0.0510 0.0029 1.0000
12.250 1.2485 0.04711 0.03961 -0.0498 0.0027 1.0000
12.500 1.2561 0.04875 0.04133 -0.0486 0.0024 1.0000
12.750 1.2591 0.05084 0.04352 -0.0472 0.0020 1.0000
13.000 1.2655 0.05264 0.04540 -0.0460 0.0020 1.0000
13.250 1.2726 0.05441 0.04725 -0.0450 0.0020 1.0000
13.500 1.2717 0.05701 0.04997 -0.0435 0.0018 1.0000
13.750 1.2745 0.05929 0.05235 -0.0424 0.0018 1.0000
14.000 1.2763 0.06173 0.05490 -0.0413 0.0017 1.0000
14.250 1.2781 0.06419 0.05745 -0.0404 0.0017 1.0000
14.500 1.2776 0.06694 0.06030 -0.0394 0.0017 1.0000
14.750 1.2784 0.06963 0.06308 -0.0386 0.0016 1.0000
15.000 1.2777 0.07253 0.06608 -0.0378 0.0016 1.0000
15.250 1.2829 0.07476 0.06839 -0.0374 0.0015 1.0000
15.500 1.2788 0.07813 0.07187 -0.0367 0.0014 1.0000
15.750 1.2756 0.08143 0.07528 -0.0361 0.0015 1.0000
16.000 1.2765 0.08430 0.07824 -0.0359 0.0014 1.0000
16.250 1.2762 0.08735 0.08139 -0.0356 0.0013 1.0000
16.500 1.2805 0.08986 0.08398 -0.0357 0.0011 1.0000
16.750 1.2791 0.09314 0.08737 -0.0357 0.0011 1.0000
17.000 1.2785 0.09633 0.09065 -0.0358 0.0011 1.0000
17.250 1.2756 0.09983 0.09426 -0.0359 0.0010 1.0000
17.500 1.2728 0.10338 0.09790 -0.0363 0.0009 1.0000
17.750 1.2693 0.10708 0.10170 -0.0366 0.0010 1.0000
18.000 1.2645 0.11100 0.10572 -0.0372 0.0009 1.0000
18.250 1.2581 0.11513 0.10996 -0.0378 0.0008 1.0000
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