WORTMANN FX 049-915 AIRFOIL (fx049915-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 049-915 AIRFOIL (fx049915-il) Reynolds number: 500,000 Max Cl/Cd: 113.48 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx049915-il-500000.txt Download as CSV file: xf-fx049915-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 049-915 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.1168 0.09032 0.08612 -0.0519 0.5000 0.0284
-10.000 -0.1337 0.08425 0.08009 -0.0563 0.4999 0.0297
-9.750 -0.1395 0.07935 0.07521 -0.0587 0.4994 0.0299
-9.500 -0.1384 0.07514 0.07101 -0.0592 0.4987 0.0302
-9.250 -0.1286 0.07282 0.06868 -0.0588 0.4978 0.0305
-9.000 -0.1155 0.07140 0.06723 -0.0583 0.4968 0.0314
-8.750 -0.1150 0.06798 0.06382 -0.0593 0.4961 0.0319
-8.500 -0.4280 0.02921 0.02361 -0.0699 0.5023 0.0210
-8.250 -0.4311 0.02453 0.01832 -0.0664 0.5016 0.0216
-8.000 -0.4121 0.02346 0.01711 -0.0652 0.5004 0.0220
-7.750 -0.3896 0.02297 0.01655 -0.0643 0.4992 0.0227
-7.500 -0.3700 0.02169 0.01503 -0.0631 0.4981 0.0235
-7.250 -0.3493 0.02046 0.01351 -0.0618 0.4970 0.0245
-7.000 -0.3277 0.01931 0.01206 -0.0607 0.4959 0.0253
-6.750 -0.3044 0.01877 0.01148 -0.0600 0.4948 0.0265
-6.500 -0.2795 0.01859 0.01124 -0.0594 0.4934 0.0275
-6.250 -0.2547 0.01811 0.01063 -0.0587 0.4926 0.0291
-6.000 -0.2308 0.01725 0.00962 -0.0579 0.4918 0.0305
-5.750 -0.2050 0.01712 0.00951 -0.0574 0.4909 0.0319
-5.500 -0.1788 0.01698 0.00933 -0.0569 0.4900 0.0338
-5.250 -0.1534 0.01651 0.00876 -0.0563 0.4889 0.0360
-5.000 -0.1266 0.01667 0.00897 -0.0560 0.4877 0.0378
-4.750 -0.1001 0.01659 0.00882 -0.0556 0.4865 0.0403
-4.500 -0.0742 0.01627 0.00843 -0.0551 0.4854 0.0428
-4.250 -0.0472 0.01653 0.00870 -0.0548 0.4844 0.0450
-4.000 -0.0204 0.01661 0.00870 -0.0544 0.4835 0.0480
-3.750 0.0058 0.01631 0.00836 -0.0540 0.4826 0.0508
-3.500 0.0324 0.01640 0.00844 -0.0537 0.4817 0.0531
-3.250 0.0593 0.01648 0.00845 -0.0534 0.4809 0.0563
-3.000 0.0857 0.01610 0.00800 -0.0530 0.4800 0.0592
-2.750 0.1122 0.01599 0.00789 -0.0528 0.4792 0.0617
-2.500 0.1389 0.01601 0.00788 -0.0525 0.4782 0.0646
-2.250 0.1654 0.01619 0.00799 -0.0522 0.4771 0.0673
-2.000 0.1918 0.01577 0.00756 -0.0519 0.4766 0.0697
-1.750 0.2176 0.01537 0.00722 -0.0515 0.4760 0.0722
-1.500 0.2438 0.01518 0.00704 -0.0511 0.4751 0.0745
-1.250 0.2701 0.01504 0.00691 -0.0507 0.4742 0.0769
-1.000 0.2963 0.01491 0.00678 -0.0503 0.4733 0.0787
-0.750 0.3226 0.01484 0.00670 -0.0500 0.4725 0.0800
-0.500 0.3474 0.01460 0.00648 -0.0494 0.4717 0.0820
-0.250 0.3722 0.01441 0.00630 -0.0487 0.4708 0.0845
0.000 0.3978 0.01434 0.00625 -0.0483 0.4700 0.0867
0.250 0.4237 0.01430 0.00622 -0.0479 0.4692 0.0890
0.500 0.4498 0.01429 0.00622 -0.0475 0.4684 0.0917
0.750 0.4762 0.01432 0.00624 -0.0472 0.4676 0.0938
1.000 0.5019 0.01426 0.00620 -0.0468 0.4668 0.0975
1.250 0.5282 0.01424 0.00619 -0.0465 0.4660 0.1023
1.500 0.5548 0.01427 0.00620 -0.0462 0.4651 0.1077
1.750 0.5806 0.01424 0.00626 -0.0459 0.4644 0.1357
2.000 0.7115 0.01249 0.00676 -0.0683 0.4632 0.9908
2.250 0.7779 0.01275 0.00695 -0.0767 0.4622 1.0000
2.500 0.8003 0.01314 0.00733 -0.0758 0.4613 1.0000
2.750 0.8231 0.01328 0.00749 -0.0750 0.4608 1.0000
3.000 0.8459 0.01344 0.00768 -0.0741 0.4601 1.0000
3.250 0.8687 0.01359 0.00786 -0.0733 0.4592 1.0000
3.500 0.8915 0.01377 0.00806 -0.0724 0.4582 1.0000
3.750 0.9143 0.01399 0.00832 -0.0716 0.4573 1.0000
4.000 0.9372 0.01422 0.00858 -0.0708 0.4564 1.0000
4.250 0.9603 0.01446 0.00884 -0.0701 0.4555 1.0000
4.500 0.9836 0.01467 0.00908 -0.0694 0.4545 1.0000
4.750 1.0072 0.01486 0.00929 -0.0687 0.4534 1.0000
5.000 1.0309 0.01505 0.00950 -0.0681 0.4524 1.0000
5.250 1.0547 0.01525 0.00972 -0.0675 0.4516 1.0000
5.500 1.0786 0.01546 0.00997 -0.0669 0.4507 1.0000
5.750 1.1031 0.01563 0.01014 -0.0664 0.4499 1.0000
6.000 1.1276 0.01579 0.01032 -0.0659 0.4490 1.0000
6.250 1.1528 0.01595 0.01048 -0.0656 0.4480 1.0000
6.500 1.1777 0.01629 0.01082 -0.0653 0.4466 1.0000
6.750 1.1995 0.01651 0.01112 -0.0644 0.4451 1.0000
7.000 1.2213 0.01672 0.01143 -0.0635 0.4435 1.0000
7.250 1.2438 0.01691 0.01171 -0.0627 0.4418 1.0000
7.500 1.2679 0.01695 0.01180 -0.0622 0.4398 1.0000
7.750 1.2948 0.01662 0.01148 -0.0620 0.4373 1.0000
8.000 1.3238 0.01609 0.01092 -0.0620 0.4348 1.0000
8.250 1.3543 0.01569 0.01043 -0.0624 0.4322 1.0000
8.500 1.3759 0.01559 0.01044 -0.0614 0.4288 1.0000
8.750 1.3983 0.01547 0.01042 -0.0605 0.4254 1.0000
9.000 1.4242 0.01509 0.01006 -0.0601 0.4219 1.0000
9.250 1.4525 0.01456 0.00947 -0.0600 0.4179 1.0000
9.500 1.4734 0.01451 0.00956 -0.0589 0.4137 1.0000
9.750 1.4960 0.01431 0.00945 -0.0581 0.4084 1.0000
10.000 1.5204 0.01398 0.00909 -0.0574 0.4025 1.0000
10.250 1.5408 0.01391 0.00919 -0.0563 0.3934 1.0000
10.500 1.5620 0.01383 0.00917 -0.0552 0.3803 1.0000
10.750 1.5797 0.01392 0.00923 -0.0537 0.3573 1.0000
11.000 1.5773 0.01496 0.00998 -0.0492 0.3097 1.0000
11.250 1.5603 0.01675 0.01157 -0.0428 0.2718 1.0000
11.500 1.5356 0.01856 0.01329 -0.0356 0.2493 1.0000
11.750 1.5097 0.02147 0.01620 -0.0312 0.2308 1.0000
12.000 1.4836 0.02651 0.02132 -0.0309 0.2187 1.0000
12.250 1.4536 0.03241 0.02728 -0.0309 0.2078 1.0000
12.500 1.4243 0.03767 0.03257 -0.0300 0.1969 1.0000
12.750 1.3954 0.04271 0.03760 -0.0290 0.1848 1.0000
13.000 1.3697 0.04745 0.04231 -0.0281 0.1719 1.0000
13.250 1.3444 0.05228 0.04709 -0.0274 0.1561 1.0000
13.500 1.3222 0.05714 0.05185 -0.0271 0.1377 1.0000
13.750 1.3032 0.06178 0.05637 -0.0268 0.1171 1.0000
14.000 1.2872 0.06624 0.06072 -0.0267 0.0987 1.0000
14.250 1.2735 0.07051 0.06486 -0.0267 0.0798 1.0000
14.500 1.2640 0.07439 0.06865 -0.0267 0.0633 1.0000
14.750 1.2501 0.07883 0.07291 -0.0269 0.0408 1.0000
15.000 1.2418 0.08272 0.07672 -0.0270 0.0315 1.0000
15.250 1.2406 0.08579 0.07981 -0.0272 0.0283 1.0000
15.500 1.2388 0.08903 0.08309 -0.0274 0.0257 1.0000
15.750 1.2395 0.09195 0.08606 -0.0277 0.0245 1.0000
16.000 1.2382 0.09514 0.08928 -0.0280 0.0230 1.0000
16.250 1.2345 0.09876 0.09295 -0.0284 0.0221 1.0000
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Polar data table (+)
Polar graphs
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