USA 34 AIRFOIL (usa34-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 34 AIRFOIL (usa34-il) Reynolds number: 200,000 Max Cl/Cd: 66.91 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa34-il-200000.txt Download as CSV file: xf-usa34-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 34 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 0.1324 0.10251 0.09843 -0.1359 0.9149 0.0857
-11.500 -0.1603 0.04392 0.03956 -0.1817 0.9009 0.0694
-11.250 -0.1674 0.03770 0.03302 -0.1900 0.8937 0.0708
-10.750 -0.2112 0.03202 0.02662 -0.1838 0.8750 0.0745
-10.500 -0.2556 0.03034 0.02451 -0.1736 0.8639 0.0758
-10.250 -0.2039 0.03123 0.02571 -0.1767 0.8611 0.0785
-10.000 -0.1979 0.02911 0.02308 -0.1753 0.8564 0.0838
-9.750 -0.1851 0.02989 0.02410 -0.1717 0.8497 0.0854
-9.500 -0.1660 0.03015 0.02435 -0.1700 0.8444 0.0896
-9.250 -0.1363 0.03025 0.02444 -0.1703 0.8408 0.0941
-9.000 -0.1134 0.02995 0.02384 -0.1701 0.8376 0.1004
-8.750 -0.0902 0.03081 0.02494 -0.1685 0.8331 0.1027
-8.500 -0.0589 0.03241 0.02679 -0.1677 0.8283 0.1053
-8.250 -0.0623 0.03101 0.02498 -0.1634 0.8229 0.1097
-8.000 -0.0299 0.03071 0.02465 -0.1645 0.8197 0.1128
-7.750 0.0236 0.03196 0.02610 -0.1682 0.8173 0.1166
-7.500 0.0101 0.03148 0.02549 -0.1611 0.8107 0.1185
-7.250 0.0046 0.03016 0.02376 -0.1559 0.8049 0.1210
-7.000 0.0352 0.02973 0.02337 -0.1566 0.8013 0.1240
-6.750 0.0829 0.03029 0.02407 -0.1598 0.7985 0.1278
-6.500 0.0838 0.02970 0.02334 -0.1551 0.7926 0.1295
-6.250 0.0863 0.02889 0.02234 -0.1506 0.7863 0.1310
-6.000 0.1033 0.02789 0.02097 -0.1488 0.7820 0.1331
-5.750 0.1324 0.02664 0.01951 -0.1495 0.7788 0.1353
-5.500 0.1467 0.02645 0.01938 -0.1469 0.7733 0.1371
-5.250 0.1601 0.02647 0.01949 -0.1439 0.7667 0.1394
-5.000 0.1873 0.02576 0.01863 -0.1437 0.7621 0.1415
-4.750 0.2225 0.02483 0.01745 -0.1451 0.7585 0.1436
-4.500 0.2272 0.02445 0.01696 -0.1405 0.7517 0.1444
-4.250 0.2422 0.02387 0.01623 -0.1379 0.7453 0.1452
-4.000 0.2740 0.02302 0.01515 -0.1384 0.7409 0.1459
-3.750 0.3153 0.02230 0.01416 -0.1408 0.7373 0.1470
-3.500 0.3101 0.02223 0.01406 -0.1341 0.7280 0.1475
-3.250 0.3388 0.02125 0.01298 -0.1341 0.7225 0.1491
-3.000 0.3805 0.02051 0.01213 -0.1367 0.7185 0.1508
-2.750 0.3851 0.02034 0.01198 -0.1319 0.7100 0.1519
-2.500 0.4108 0.01989 0.01147 -0.1311 0.7035 0.1537
-2.250 0.4519 0.01936 0.01081 -0.1335 0.6989 0.1565
-2.000 0.4562 0.01924 0.01068 -0.1285 0.6899 0.1583
-1.750 0.4833 0.01888 0.01022 -0.1281 0.6834 0.1612
-1.500 0.5246 0.01829 0.00954 -0.1306 0.6787 0.1658
-1.250 0.5241 0.01822 0.00956 -0.1247 0.6694 0.1685
-1.000 0.5529 0.01790 0.00920 -0.1247 0.6632 0.1750
-0.750 0.5790 0.01759 0.00886 -0.1241 0.6569 0.1824
-0.500 0.5873 0.01747 0.00881 -0.1200 0.6486 0.1891
-0.250 0.6180 0.01714 0.00846 -0.1204 0.6430 0.2013
0.000 0.6327 0.01711 0.00846 -0.1176 0.6362 0.2123
0.250 0.6459 0.01700 0.00841 -0.1145 0.6292 0.2236
0.500 0.6788 0.01683 0.00822 -0.1154 0.6239 0.2409
0.750 0.6859 0.01689 0.00830 -0.1111 0.6169 0.2540
1.000 0.7021 0.01685 0.00831 -0.1086 0.6104 0.2716
1.250 0.7361 0.01673 0.00820 -0.1098 0.6056 0.2982
1.500 0.7459 0.01683 0.00839 -0.1062 0.5995 0.3196
1.750 0.7617 0.01686 0.00849 -0.1037 0.5936 0.3454
2.000 0.7922 0.01676 0.00841 -0.1042 0.5887 0.3789
2.250 0.8132 0.01677 0.00854 -0.1030 0.5835 0.4157
2.500 0.8259 0.01677 0.00879 -0.1001 0.5777 0.4672
2.750 1.0958 0.01668 0.00949 -0.1518 0.5694 1.0000
3.000 1.1096 0.01700 0.00979 -0.1491 0.5643 1.0000
3.250 1.1246 0.01727 0.01003 -0.1466 0.5590 1.0000
3.500 1.1490 0.01751 0.01017 -0.1460 0.5544 1.0000
3.750 1.1884 0.01776 0.01025 -0.1485 0.5501 1.0000
4.000 1.1918 0.01814 0.01070 -0.1437 0.5453 1.0000
4.250 1.2049 0.01842 0.01095 -0.1409 0.5398 1.0000
4.500 1.2326 0.01865 0.01108 -0.1410 0.5348 1.0000
4.750 1.2603 0.01900 0.01135 -0.1412 0.5300 1.0000
5.000 1.2623 0.01936 0.01177 -0.1363 0.5253 1.0000
5.250 1.2776 0.01967 0.01207 -0.1340 0.5207 1.0000
5.500 1.3062 0.01996 0.01228 -0.1344 0.5166 1.0000
5.750 1.3433 0.02037 0.01259 -0.1365 0.5122 1.0000
6.000 1.3369 0.02075 0.01307 -0.1300 0.5078 1.0000
6.250 1.3466 0.02111 0.01347 -0.1268 0.5033 1.0000
6.500 1.3697 0.02144 0.01376 -0.1261 0.4994 1.0000
6.750 1.4077 0.02175 0.01398 -0.1284 0.4954 1.0000
7.000 1.4128 0.02223 0.01452 -0.1244 0.4911 1.0000
7.250 1.4118 0.02269 0.01506 -0.1193 0.4864 1.0000
7.500 1.4266 0.02299 0.01535 -0.1171 0.4815 1.0000
7.750 1.4596 0.02317 0.01543 -0.1183 0.4769 1.0000
8.000 1.4659 0.02369 0.01600 -0.1147 0.4724 1.0000
8.250 1.4616 0.02425 0.01666 -0.1094 0.4672 1.0000
8.500 1.4757 0.02459 0.01700 -0.1073 0.4625 1.0000
8.750 1.5061 0.02471 0.01704 -0.1080 0.4580 1.0000
9.000 1.5106 0.02535 0.01775 -0.1044 0.4537 1.0000
9.250 1.5063 0.02611 0.01863 -0.0996 0.4488 1.0000
9.500 1.5180 0.02656 0.01910 -0.0974 0.4441 1.0000
9.750 1.5437 0.02670 0.01918 -0.0973 0.4400 1.0000
10.000 1.5513 0.02739 0.01993 -0.0946 0.4356 1.0000
10.250 1.5451 0.02845 0.02113 -0.0901 0.4308 1.0000
10.500 1.5540 0.02908 0.02180 -0.0877 0.4262 1.0000
10.750 1.5767 0.02927 0.02195 -0.0873 0.4221 1.0000
11.000 1.5848 0.03005 0.02279 -0.0850 0.4176 1.0000
11.250 1.5748 0.03150 0.02438 -0.0806 0.4122 1.0000
11.500 1.5837 0.03221 0.02513 -0.0786 0.4072 1.0000
11.750 1.6121 0.03210 0.02492 -0.0788 0.4025 1.0000
12.000 1.5935 0.03419 0.02721 -0.0739 0.3967 1.0000
12.250 1.5924 0.03549 0.02858 -0.0711 0.3905 1.0000
12.500 1.6161 0.03548 0.02848 -0.0708 0.3852 1.0000
12.750 1.5980 0.03797 0.03115 -0.0667 0.3786 1.0000
13.000 1.5978 0.03940 0.03263 -0.0644 0.3717 1.0000
13.250 1.6073 0.04032 0.03353 -0.0630 0.3652 1.0000
13.500 1.5935 0.04296 0.03632 -0.0600 0.3575 1.0000
13.750 1.6104 0.04337 0.03664 -0.0592 0.3509 1.0000
14.000 1.5913 0.04671 0.04016 -0.0562 0.3423 1.0000
14.250 1.6010 0.04773 0.04113 -0.0551 0.3348 1.0000
14.500 1.5861 0.05103 0.04456 -0.0528 0.3253 1.0000
14.750 1.5966 0.05202 0.04546 -0.0518 0.3170 1.0000
15.000 1.5783 0.05589 0.04946 -0.0497 0.3062 1.0000
15.250 1.5753 0.05835 0.05191 -0.0484 0.2962 1.0000
15.500 1.5723 0.06085 0.05437 -0.0472 0.2859 1.0000
15.750 1.5621 0.06426 0.05785 -0.0460 0.2758 1.0000
16.000 1.5641 0.06632 0.05981 -0.0450 0.2673 1.0000
16.250 1.5548 0.06979 0.06335 -0.0441 0.2577 1.0000
16.500 1.5542 0.07226 0.06578 -0.0433 0.2501 1.0000
16.750 1.5498 0.07528 0.06884 -0.0426 0.2427 1.0000
17.000 1.5537 0.07721 0.07069 -0.0420 0.2362 1.0000
17.250 1.5458 0.08076 0.07435 -0.0415 0.2293 1.0000
17.500 1.5509 0.08261 0.07611 -0.0410 0.2234 1.0000
17.750 1.5475 0.08565 0.07924 -0.0407 0.2177 1.0000
18.000 1.5450 0.08856 0.08219 -0.0404 0.2118 1.0000
18.250 1.5541 0.08985 0.08337 -0.0400 0.2064 1.0000
18.500 1.5444 0.09381 0.08748 -0.0400 0.2008 1.0000
18.750 1.5466 0.09608 0.08972 -0.0398 0.1951 1.0000
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