WORTMANN FX 082-512 AIRFOIL (fx082512-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 082-512 AIRFOIL (fx082512-il) Reynolds number: 200,000 Max Cl/Cd: 63.64 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx082512-il-200000.txt Download as CSV file: xf-fx082512-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 082-512 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 -0.6419 0.08461 0.08075 -0.0589 1.0000 0.0389
-11.500 -0.6682 0.07814 0.07424 -0.0614 1.0000 0.0386
-11.250 -0.6933 0.07262 0.06867 -0.0633 1.0000 0.0383
-11.000 -0.7175 0.06782 0.06383 -0.0646 1.0000 0.0379
-10.750 -0.7458 0.06332 0.05926 -0.0654 1.0000 0.0378
-10.500 -0.7741 0.05974 0.05563 -0.0649 1.0000 0.0376
-10.250 -0.8004 0.05633 0.05217 -0.0644 1.0000 0.0371
-10.000 -0.8159 0.05099 0.04663 -0.0695 1.0000 0.0372
-9.750 -0.8162 0.04466 0.03983 -0.0777 1.0000 0.0380
-9.500 -0.8039 0.03969 0.03432 -0.0832 1.0000 0.0392
-9.250 -0.7872 0.03720 0.03177 -0.0845 1.0000 0.0406
-9.000 -0.7662 0.03572 0.03019 -0.0859 1.0000 0.0422
-8.750 -0.7432 0.03399 0.02826 -0.0875 1.0000 0.0446
-8.500 -0.7156 0.03188 0.02570 -0.0904 1.0000 0.0482
-8.250 -0.6932 0.03043 0.02428 -0.0912 1.0000 0.0509
-8.000 -0.6675 0.02939 0.02311 -0.0923 1.0000 0.0546
-7.750 -0.6390 0.02787 0.02128 -0.0942 1.0000 0.0596
-7.500 -0.6143 0.02672 0.02018 -0.0950 1.0000 0.0644
-7.250 -0.5865 0.02602 0.01926 -0.0962 1.0000 0.0698
-7.000 -0.5598 0.02431 0.01753 -0.0973 1.0000 0.0754
-6.750 -0.5330 0.02353 0.01668 -0.0982 1.0000 0.0809
-6.500 -0.5056 0.02316 0.01610 -0.0989 1.0000 0.0851
-6.250 -0.4777 0.02168 0.01473 -0.1001 1.0000 0.0908
-6.000 -0.4499 0.02108 0.01411 -0.1010 1.0000 0.0958
-5.750 -0.4224 0.02068 0.01362 -0.1016 1.0000 0.0996
-5.500 -0.3850 0.01996 0.01294 -0.1044 0.9987 0.1042
-5.250 -0.3440 0.01954 0.01252 -0.1079 0.9965 0.1093
-5.000 -0.3029 0.01935 0.01224 -0.1112 0.9943 0.1136
-4.750 -0.2629 0.01893 0.01173 -0.1145 0.9914 0.1202
-4.500 -0.2226 0.01853 0.01125 -0.1179 0.9891 0.1305
-4.250 -0.1785 0.01779 0.01111 -0.1226 0.9878 0.2714
-4.000 -0.1444 0.01836 0.01156 -0.1238 0.9836 0.2995
-3.750 -0.1113 0.01919 0.01237 -0.1246 0.9791 0.3163
-3.500 -0.0771 0.01997 0.01303 -0.1257 0.9752 0.3290
-3.250 -0.0487 0.02064 0.01385 -0.1255 0.9700 0.3362
-3.000 -0.0108 0.02105 0.01411 -0.1276 0.9673 0.3447
-2.750 0.0157 0.02140 0.01458 -0.1272 0.9617 0.3492
-2.500 0.0491 0.02181 0.01499 -0.1283 0.9578 0.3566
-2.250 0.0872 0.02198 0.01513 -0.1304 0.9555 0.3624
-2.000 0.1122 0.02218 0.01540 -0.1299 0.9492 0.3664
-1.750 0.1474 0.02225 0.01545 -0.1315 0.9456 0.3711
-1.500 0.1874 0.02222 0.01532 -0.1342 0.9433 0.3767
-1.250 0.2144 0.02228 0.01547 -0.1341 0.9376 0.3799
-1.000 0.2471 0.02228 0.01552 -0.1352 0.9330 0.3835
-0.750 0.2937 0.02206 0.01522 -0.1387 0.9296 0.3900
-0.500 0.3253 0.02184 0.01509 -0.1394 0.9223 0.3945
-0.250 0.3656 0.02155 0.01490 -0.1414 0.9168 0.3996
0.000 0.4170 0.02086 0.01419 -0.1457 0.9139 0.4032
0.250 0.4486 0.02047 0.01376 -0.1464 0.9049 0.4053
0.500 0.4976 0.01962 0.01292 -0.1501 0.9008 0.4076
0.750 0.5488 0.01864 0.01204 -0.1540 0.8983 0.4103
1.000 0.5854 0.01777 0.01125 -0.1548 0.8869 0.4126
1.250 0.6361 0.01643 0.00999 -0.1581 0.8785 0.4153
1.500 0.6864 0.01529 0.00889 -0.1615 0.8686 0.4182
1.750 0.7287 0.01447 0.00809 -0.1634 0.8520 0.4210
2.000 0.7610 0.01394 0.00759 -0.1636 0.8267 0.4232
2.250 0.8181 0.01323 0.00684 -0.1685 0.7743 0.4266
2.500 0.8591 0.01350 0.00647 -0.1701 0.6412 0.4301
2.750 0.8576 0.01491 0.00683 -0.1637 0.4572 0.4319
3.000 0.8569 0.01664 0.00755 -0.1584 0.2741 0.4336
3.250 0.8664 0.01822 0.00829 -0.1554 0.1342 0.4357
3.500 0.8882 0.01878 0.00878 -0.1542 0.1234 0.4381
3.750 0.9104 0.01913 0.00924 -0.1530 0.1176 0.4405
4.000 0.9303 0.01969 0.00985 -0.1514 0.1120 0.4431
4.250 0.9481 0.02047 0.01063 -0.1495 0.1075 0.4458
4.500 0.9697 0.02099 0.01124 -0.1483 0.1029 0.4493
4.750 0.9904 0.02176 0.01198 -0.1470 0.0975 0.4530
5.000 1.0129 0.02296 0.01317 -0.1462 0.0919 0.4563
5.250 1.0369 0.02353 0.01386 -0.1454 0.0865 0.4601
5.500 1.0661 0.02498 0.01524 -0.1460 0.0795 0.4644
5.750 1.0923 0.02580 0.01618 -0.1455 0.0735 0.4687
6.000 1.1188 0.02677 0.01717 -0.1455 0.0671 0.4730
6.250 1.1476 0.02803 0.01859 -0.1456 0.0607 0.4781
6.500 1.1726 0.02886 0.01948 -0.1450 0.0559 0.4838
6.750 1.2033 0.03051 0.02123 -0.1457 0.0514 0.4901
7.000 1.2266 0.03123 0.02216 -0.1446 0.0475 0.4973
7.250 1.2501 0.03208 0.02313 -0.1439 0.0449 0.5049
7.500 1.2813 0.03441 0.02559 -0.1447 0.0424 0.5146
7.750 1.3057 0.03595 0.02755 -0.1436 0.0398 0.5242
8.000 1.3279 0.03709 0.02890 -0.1426 0.0377 0.5367
8.250 1.3493 0.03834 0.03033 -0.1417 0.0363 0.5536
8.500 1.3730 0.04117 0.03341 -0.1415 0.0350 0.5806
8.750 1.3895 0.04494 0.03786 -0.1394 0.0343 0.6269
9.000 1.3969 0.04833 0.04215 -0.1355 0.0336 0.7790
9.250 1.3937 0.05131 0.04566 -0.1297 0.0330 1.0000
9.500 1.3951 0.05563 0.05041 -0.1258 0.0325 1.0000
9.750 1.3909 0.06033 0.05549 -0.1216 0.0327 1.0000
10.000 1.3830 0.06490 0.06039 -0.1173 0.0331 1.0000
10.250 1.3707 0.06920 0.06496 -0.1128 0.0335 1.0000
10.500 1.3549 0.07309 0.06906 -0.1082 0.0338 1.0000
10.750 1.3392 0.07731 0.07345 -0.1044 0.0342 1.0000
11.000 1.0224 0.10751 0.10481 -0.0951 0.0591 0.5672
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Polar data table (+)
Polar graphs
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