WORTMANN FX 80-080 (fx80080-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 80-080 (fx80080-il) Reynolds number: 200,000 Max Cl/Cd: 80.43 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx80080-il-200000.txt Download as CSV file: xf-fx80080-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 80-080
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4502 0.10257 0.09901 -0.0362 1.0000 0.0315
-9.000 -0.4486 0.09893 0.09540 -0.0379 1.0000 0.0315
-8.750 -0.4511 0.09248 0.08901 -0.0355 1.0000 0.0330
-8.500 -0.4470 0.08950 0.08605 -0.0350 1.0000 0.0338
-8.250 -0.4441 0.08671 0.08326 -0.0347 1.0000 0.0354
-8.000 -0.4462 0.08358 0.08019 -0.0353 1.0000 0.0361
-7.750 -0.4516 0.08078 0.07747 -0.0355 1.0000 0.0377
-7.500 -0.4614 0.07767 0.07444 -0.0360 1.0000 0.0376
-7.250 -0.4699 0.07431 0.07115 -0.0375 1.0000 0.0386
-7.000 -0.4832 0.07177 0.06865 -0.0366 1.0000 0.0398
-6.750 -0.4960 0.06943 0.06633 -0.0346 1.0000 0.0386
-6.500 -0.5040 0.06663 0.06349 -0.0342 1.0000 0.0410
-6.250 -0.4970 0.06379 0.06026 -0.0380 0.9993 0.0437
-6.000 -0.4789 0.05560 0.05182 -0.0436 0.9957 0.0448
-5.750 -0.4602 0.05158 0.04790 -0.0451 0.9927 0.0469
-5.500 -0.4329 0.04781 0.04398 -0.0485 0.9893 0.0500
-5.250 -0.3931 0.04650 0.04176 -0.0522 0.9837 0.0571
-5.000 -0.3750 0.03903 0.03446 -0.0550 0.9810 0.0602
-4.750 -0.3441 0.03614 0.03138 -0.0573 0.9784 0.0650
-4.500 -0.3158 0.03286 0.02767 -0.0590 0.9744 0.0741
-4.250 -0.2794 0.02584 0.01967 -0.0584 0.9717 0.0390
-4.000 -0.2466 0.02335 0.01670 -0.0594 0.9690 0.0399
-3.750 -0.2126 0.02067 0.01353 -0.0601 0.9671 0.0381
-3.500 -0.1774 0.01873 0.01124 -0.0612 0.9655 0.0384
-3.250 -0.1469 0.01748 0.00982 -0.0615 0.9625 0.0407
-3.000 -0.1190 0.01645 0.00868 -0.0615 0.9586 0.0459
-2.750 -0.0871 0.01555 0.00778 -0.0625 0.9557 0.0542
-2.500 -0.0531 0.01461 0.00686 -0.0639 0.9533 0.0730
-2.250 -0.0187 0.01344 0.00615 -0.0659 0.9514 0.1684
-2.000 -0.0107 0.01160 0.00649 -0.0624 0.9459 0.7203
-1.750 0.0113 0.01166 0.00670 -0.0602 0.9416 0.8177
-1.500 0.0385 0.01168 0.00670 -0.0593 0.9387 0.8614
-1.250 0.0567 0.01173 0.00671 -0.0567 0.9336 0.8953
-1.000 0.0801 0.01169 0.00667 -0.0552 0.9293 0.9289
-0.750 0.1408 0.01167 0.00658 -0.0614 0.9305 0.9735
-0.500 0.2353 0.01157 0.00633 -0.0748 0.9381 1.0000
-0.250 0.2509 0.01163 0.00635 -0.0732 0.9298 1.0000
0.000 0.2871 0.01159 0.00625 -0.0754 0.9266 1.0000
0.250 0.3289 0.01152 0.00614 -0.0786 0.9245 1.0000
0.500 0.3438 0.01163 0.00623 -0.0767 0.9158 1.0000
0.750 0.3821 0.01154 0.00613 -0.0790 0.9123 1.0000
1.000 0.4255 0.01140 0.00600 -0.0823 0.9098 1.0000
1.250 0.4422 0.01152 0.00613 -0.0804 0.9001 1.0000
1.500 0.4852 0.01132 0.00595 -0.0833 0.8964 1.0000
1.750 0.5076 0.01137 0.00602 -0.0823 0.8868 1.0000
2.000 0.5437 0.01116 0.00584 -0.0835 0.8788 1.0000
2.250 0.5805 0.01083 0.00557 -0.0846 0.8685 1.0000
2.500 0.6098 0.01058 0.00535 -0.0841 0.8547 1.0000
2.750 0.6377 0.01037 0.00516 -0.0834 0.8399 1.0000
3.000 0.6629 0.01026 0.00508 -0.0824 0.8250 1.0000
3.250 0.6869 0.01014 0.00502 -0.0810 0.8079 1.0000
3.500 0.7117 0.01000 0.00495 -0.0798 0.7890 1.0000
3.750 0.7353 0.00985 0.00485 -0.0783 0.7652 1.0000
4.000 0.7584 0.00974 0.00478 -0.0767 0.7348 1.0000
4.250 0.7802 0.00970 0.00471 -0.0749 0.6895 1.0000
4.500 0.7952 0.01005 0.00457 -0.0714 0.5611 1.0000
4.750 0.7954 0.01159 0.00503 -0.0661 0.3692 1.0000
5.000 0.7994 0.01337 0.00584 -0.0622 0.1974 1.0000
5.250 0.8117 0.01480 0.00673 -0.0598 0.1148 1.0000
5.500 0.8280 0.01594 0.00765 -0.0580 0.0821 1.0000
5.750 0.8454 0.01706 0.00873 -0.0561 0.0636 1.0000
6.000 0.8623 0.01843 0.01008 -0.0542 0.0531 1.0000
6.250 0.8832 0.01937 0.01105 -0.0530 0.0451 1.0000
6.500 0.9040 0.02113 0.01291 -0.0518 0.0400 1.0000
6.750 0.9268 0.02217 0.01404 -0.0509 0.0344 1.0000
7.000 0.9515 0.02504 0.01702 -0.0505 0.0301 1.0000
7.250 0.9770 0.02709 0.01938 -0.0496 0.0282 1.0000
7.500 0.9991 0.02881 0.02137 -0.0485 0.0250 1.0000
7.750 1.0181 0.03032 0.02297 -0.0474 0.0224 1.0000
8.000 1.0357 0.03408 0.02712 -0.0459 0.0216 1.0000
8.250 1.0488 0.03793 0.03143 -0.0436 0.0215 1.0000
8.500 0.9970 0.03292 0.02797 -0.0328 0.0253 1.0000
8.750 0.9880 0.03914 0.03462 -0.0289 0.0275 1.0000
9.000 0.9772 0.04479 0.04051 -0.0257 0.0292 1.0000
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Polar data table (+)
Polar graphs
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