UAG 88-143/20 (uag8814320-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: UAG 88-143/20 (uag8814320-il) Reynolds number: 1,000,000 Max Cl/Cd: 169.26 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-uag8814320-il-1000000-n5.txt Download as CSV file: xf-uag8814320-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0092 0.04931 0.04655 -0.1708 0.7799 0.0034
-9.250 -0.0515 0.04290 0.04011 -0.1709 0.7779 0.0034
-9.000 -0.1308 0.02671 0.02338 -0.1674 0.7753 0.0034
-8.750 -0.1320 0.02336 0.01969 -0.1648 0.7738 0.0034
-8.500 -0.1261 0.02093 0.01692 -0.1624 0.7726 0.0033
-8.250 -0.1141 0.01915 0.01485 -0.1605 0.7715 0.0032
-8.000 -0.0990 0.01767 0.01307 -0.1587 0.7705 0.0030
-7.750 -0.0799 0.01668 0.01188 -0.1576 0.7695 0.0030
-7.500 -0.0591 0.01584 0.01086 -0.1566 0.7684 0.0029
-7.250 -0.0375 0.01513 0.01001 -0.1558 0.7674 0.0029
-7.000 -0.0151 0.01449 0.00924 -0.1550 0.7663 0.0028
-6.750 0.0076 0.01390 0.00855 -0.1543 0.7652 0.0028
-6.500 0.0307 0.01335 0.00791 -0.1536 0.7638 0.0028
-6.250 0.0546 0.01287 0.00733 -0.1531 0.7625 0.0027
-6.000 0.0786 0.01240 0.00679 -0.1525 0.7612 0.0027
-5.750 0.1029 0.01195 0.00628 -0.1520 0.7600 0.0027
-5.500 0.1276 0.01154 0.00580 -0.1516 0.7587 0.0027
-5.250 0.1523 0.01114 0.00534 -0.1512 0.7575 0.0027
-5.000 0.1775 0.01077 0.00491 -0.1508 0.7563 0.0026
-4.750 0.2030 0.01045 0.00453 -0.1505 0.7551 0.0026
-4.500 0.2282 0.01014 0.00418 -0.1501 0.7538 0.0026
-4.250 0.2535 0.00988 0.00390 -0.1498 0.7523 0.0026
-4.000 0.2787 0.00960 0.00359 -0.1494 0.7507 0.0026
-3.750 0.3043 0.00937 0.00333 -0.1491 0.7490 0.0026
-3.500 0.3301 0.00915 0.00307 -0.1488 0.7473 0.0026
-3.250 0.3561 0.00897 0.00284 -0.1485 0.7457 0.0027
-3.000 0.3823 0.00879 0.00263 -0.1483 0.7441 0.0027
-2.750 0.4088 0.00865 0.00245 -0.1482 0.7426 0.0028
-2.500 0.4352 0.00854 0.00230 -0.1481 0.7409 0.0029
-2.250 0.4613 0.00844 0.00220 -0.1478 0.7390 0.0030
-2.000 0.4875 0.00835 0.00211 -0.1477 0.7367 0.0032
-1.750 0.5137 0.00825 0.00200 -0.1475 0.7343 0.0040
-1.500 0.5396 0.00813 0.00189 -0.1473 0.7320 0.0135
-1.250 0.5650 0.00796 0.00180 -0.1470 0.7299 0.0373
-1.000 0.5903 0.00781 0.00176 -0.1467 0.7277 0.0655
-0.750 0.6160 0.00774 0.00175 -0.1465 0.7250 0.0811
-0.500 0.6410 0.00761 0.00173 -0.1461 0.7220 0.1148
-0.250 0.6650 0.00742 0.00171 -0.1456 0.7190 0.1831
0.000 0.6870 0.00710 0.00170 -0.1447 0.7161 0.3031
0.250 0.7094 0.00687 0.00172 -0.1439 0.7129 0.4019
0.500 0.7314 0.00665 0.00174 -0.1430 0.7092 0.4980
0.750 0.7514 0.00639 0.00177 -0.1416 0.7055 0.6119
1.000 0.7643 0.00600 0.00182 -0.1386 0.7016 0.7777
1.250 0.8226 0.00580 0.00207 -0.1454 0.6980 0.9548
1.500 0.8672 0.00589 0.00215 -0.1494 0.6937 0.9694
1.750 0.9072 0.00600 0.00222 -0.1524 0.6894 0.9776
2.000 0.9414 0.00610 0.00231 -0.1541 0.6848 0.9842
2.250 0.9783 0.00618 0.00237 -0.1565 0.6795 0.9872
2.500 1.0102 0.00628 0.00242 -0.1577 0.6737 0.9902
2.750 1.0411 0.00637 0.00251 -0.1588 0.6668 0.9930
3.000 1.0721 0.00649 0.00259 -0.1599 0.6597 0.9955
3.250 1.1043 0.00658 0.00269 -0.1613 0.6519 0.9977
3.500 1.1357 0.00671 0.00279 -0.1625 0.6441 0.9996
3.750 1.1538 0.00686 0.00290 -0.1608 0.6345 1.0000
4.000 1.1678 0.00698 0.00302 -0.1581 0.6261 1.0000
4.250 1.1779 0.00716 0.00316 -0.1546 0.6166 1.0000
4.500 1.1850 0.00735 0.00332 -0.1504 0.6061 1.0000
4.750 1.1849 0.00753 0.00348 -0.1447 0.5950 1.0000
5.000 1.1855 0.00777 0.00368 -0.1391 0.5829 1.0000
5.250 1.1885 0.00808 0.00396 -0.1343 0.5701 1.0000
5.500 1.1915 0.00849 0.00433 -0.1296 0.5557 1.0000
5.750 1.1966 0.00898 0.00478 -0.1256 0.5422 1.0000
6.000 1.2003 0.00964 0.00539 -0.1216 0.5259 1.0000
6.250 1.2049 0.01043 0.00613 -0.1180 0.5090 1.0000
6.500 1.2130 0.01120 0.00685 -0.1152 0.4939 1.0000
6.750 1.2202 0.01206 0.00765 -0.1123 0.4765 1.0000
7.000 1.2146 0.01350 0.00892 -0.1075 0.4401 1.0000
7.250 1.2111 0.01490 0.01014 -0.1032 0.4055 1.0000
7.500 1.2214 0.01569 0.01087 -0.1010 0.3887 1.0000
7.750 1.2127 0.01740 0.01231 -0.0961 0.3404 1.0000
8.000 1.2184 0.01845 0.01323 -0.0933 0.3139 1.0000
8.250 1.2173 0.01989 0.01446 -0.0897 0.2763 1.0000
8.500 1.2162 0.02138 0.01572 -0.0862 0.2345 1.0000
8.750 1.2141 0.02302 0.01711 -0.0827 0.1912 1.0000
9.000 1.2197 0.02426 0.01821 -0.0803 0.1625 1.0000
9.250 1.2156 0.02613 0.01981 -0.0768 0.1172 1.0000
9.500 1.2158 0.02782 0.02128 -0.0739 0.0794 1.0000
9.750 1.2147 0.02965 0.02291 -0.0710 0.0437 1.0000
10.000 1.2109 0.03173 0.02479 -0.0678 0.0077 1.0000
10.250 1.2205 0.03296 0.02602 -0.0662 0.0031 1.0000
10.500 1.2344 0.03390 0.02700 -0.0652 0.0028 1.0000
10.750 1.2465 0.03498 0.02812 -0.0640 0.0021 1.0000
11.000 1.2578 0.03614 0.02935 -0.0627 0.0019 1.0000
11.250 1.2704 0.03721 0.03046 -0.0617 0.0018 1.0000
11.500 1.2821 0.03837 0.03167 -0.0605 0.0016 1.0000
11.750 1.2926 0.03965 0.03299 -0.0594 0.0014 1.0000
12.000 1.3038 0.04087 0.03427 -0.0583 0.0013 1.0000
12.250 1.3140 0.04220 0.03564 -0.0572 0.0012 1.0000
12.500 1.3215 0.04376 0.03727 -0.0558 0.0011 1.0000
12.750 1.3222 0.04594 0.03954 -0.0539 0.0008 1.0000
13.000 1.3315 0.04741 0.04108 -0.0529 0.0008 1.0000
13.250 1.3466 0.04837 0.04205 -0.0525 0.0008 1.0000
13.500 1.3502 0.05041 0.04418 -0.0511 0.0007 1.0000
13.750 1.3609 0.05180 0.04560 -0.0503 0.0007 1.0000
14.000 1.3654 0.05379 0.04768 -0.0491 0.0006 1.0000
14.250 1.3704 0.05577 0.04972 -0.0481 0.0006 1.0000
14.500 1.3757 0.05776 0.05178 -0.0471 0.0006 1.0000
14.750 1.3798 0.05990 0.05400 -0.0461 0.0006 1.0000
15.000 1.3818 0.06229 0.05647 -0.0452 0.0005 1.0000
15.250 1.3908 0.06396 0.05818 -0.0447 0.0005 1.0000
15.500 1.3885 0.06686 0.06119 -0.0436 0.0005 1.0000
15.750 1.3873 0.06972 0.06417 -0.0427 0.0005 1.0000
16.000 1.3902 0.07218 0.06670 -0.0422 0.0005 1.0000
16.250 1.3903 0.07498 0.06958 -0.0416 0.0005 1.0000
16.500 1.3937 0.07742 0.07210 -0.0412 0.0004 1.0000
16.750 1.3914 0.08059 0.07536 -0.0407 0.0004 1.0000
17.000 1.3930 0.08330 0.07815 -0.0405 0.0004 1.0000
17.250 1.3898 0.08667 0.08161 -0.0402 0.0004 1.0000
17.500 1.3864 0.09012 0.08516 -0.0401 0.0004 1.0000
17.750 1.3803 0.09400 0.08916 -0.0400 0.0004 1.0000
18.000 1.3815 0.09693 0.09215 -0.0402 0.0004 1.0000
18.250 1.3833 0.09978 0.09507 -0.0405 0.0003 1.0000
18.500 1.3796 0.10341 0.09879 -0.0408 0.0003 1.0000
18.750 1.3675 0.10830 0.10382 -0.0413 0.0003 1.0000
19.000 1.3692 0.11127 0.10685 -0.0419 0.0003 1.0000
|
Polar data table (+)
Polar graphs
<< Back to UAG 88-143/20 (uag8814320-il)