WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Reynolds number: 500,000 Max Cl/Cd: 108.76 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx08s176-il-500000.txt Download as CSV file: xf-fx08s176-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 08-S-176 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0150 0.09123 0.08724 -0.0847 0.5975 0.0199
-10.750 -0.0091 0.08840 0.08442 -0.0855 0.5968 0.0207
-10.500 -0.0066 0.08491 0.08095 -0.0868 0.5962 0.0211
-10.250 -0.0057 0.08116 0.07722 -0.0883 0.5955 0.0224
-10.000 -0.0060 0.07717 0.07326 -0.0899 0.5949 0.0228
-9.750 -0.0118 0.07219 0.06830 -0.0925 0.5944 0.0238
-9.500 -0.0204 0.06648 0.06263 -0.0964 0.5939 0.0244
-9.250 -0.0271 0.06113 0.05730 -0.0997 0.5933 0.0245
-9.000 -0.0425 0.05441 0.05059 -0.1052 0.5929 0.0245
-8.750 -0.0593 0.04972 0.04585 -0.1074 0.5923 0.0245
-8.500 -0.0774 0.04588 0.04196 -0.1074 0.5916 0.0245
-8.250 -0.0943 0.04296 0.03897 -0.1055 0.5909 0.0245
-8.000 -0.1113 0.03980 0.03569 -0.1027 0.5901 0.0245
-7.500 -0.1568 0.04300 0.03828 -0.1023 0.5898 0.0253
-7.250 -0.1458 0.04125 0.03648 -0.1013 0.5889 0.0257
-7.000 -0.1333 0.03974 0.03488 -0.1003 0.5879 0.0263
-6.750 -0.1180 0.03865 0.03371 -0.0996 0.5869 0.0275
-6.500 -0.1040 0.03662 0.03145 -0.0981 0.5861 0.0300
-6.250 -0.1122 0.02741 0.02134 -0.0924 0.5856 0.0231
-6.000 -0.0962 0.02448 0.01798 -0.0906 0.5846 0.0230
-5.750 -0.0751 0.02258 0.01576 -0.0896 0.5838 0.0235
-5.500 -0.0503 0.02229 0.01527 -0.0890 0.5830 0.0247
-5.250 -0.0279 0.01970 0.01244 -0.0883 0.5822 0.0256
-5.000 -0.0026 0.01879 0.01148 -0.0881 0.5812 0.0265
-4.750 0.0231 0.01815 0.01077 -0.0879 0.5801 0.0274
-4.500 0.0491 0.01762 0.01020 -0.0876 0.5789 0.0286
-4.250 0.0752 0.01720 0.00973 -0.0874 0.5776 0.0300
-4.000 0.1010 0.01669 0.00915 -0.0871 0.5765 0.0309
-3.750 0.1269 0.01630 0.00870 -0.0869 0.5755 0.0316
-3.500 0.1505 0.01560 0.00796 -0.0863 0.5745 0.0328
-3.250 0.1751 0.01518 0.00753 -0.0859 0.5736 0.0349
-3.000 0.2011 0.01496 0.00729 -0.0858 0.5727 0.0371
-2.750 0.2273 0.01477 0.00705 -0.0857 0.5718 0.0393
-2.500 0.2536 0.01459 0.00681 -0.0856 0.5709 0.0418
-2.250 0.2798 0.01449 0.00672 -0.0855 0.5697 0.0484
-2.000 0.3059 0.01437 0.00665 -0.0854 0.5687 0.0650
-1.750 0.3315 0.01413 0.00652 -0.0853 0.5677 0.0935
-1.500 0.3563 0.01376 0.00648 -0.0853 0.5666 0.1779
-1.250 0.3738 0.01200 0.00634 -0.0850 0.5654 0.6520
-1.000 0.3925 0.01201 0.00688 -0.0826 0.5642 0.7979
-0.750 0.4188 0.01233 0.00717 -0.0821 0.5628 0.8315
-0.500 0.4420 0.01270 0.00752 -0.0807 0.5616 0.8484
-0.250 0.4641 0.01306 0.00786 -0.0791 0.5603 0.8625
0.000 0.4850 0.01332 0.00810 -0.0771 0.5591 0.8723
0.250 0.5077 0.01344 0.00818 -0.0757 0.5577 0.8797
0.500 0.5313 0.01359 0.00826 -0.0746 0.5564 0.8877
0.750 0.5548 0.01379 0.00839 -0.0735 0.5548 0.8936
1.000 0.5759 0.01380 0.00843 -0.0721 0.5530 0.8992
1.250 0.6009 0.01384 0.00846 -0.0717 0.5511 0.9055
1.500 0.6237 0.01382 0.00844 -0.0707 0.5493 0.9083
1.750 0.6473 0.01386 0.00848 -0.0700 0.5479 0.9121
2.000 0.6728 0.01393 0.00853 -0.0697 0.5465 0.9181
2.250 0.6951 0.01387 0.00846 -0.0686 0.5452 0.9220
2.500 0.7216 0.01382 0.00838 -0.0686 0.5439 0.9241
2.750 0.7495 0.01379 0.00831 -0.0689 0.5428 0.9262
3.000 0.7783 0.01379 0.00826 -0.0694 0.5415 0.9281
3.250 0.8073 0.01394 0.00836 -0.0702 0.5402 0.9300
3.500 0.8332 0.01399 0.00847 -0.0703 0.5386 0.9326
3.750 0.8540 0.01396 0.00850 -0.0692 0.5368 0.9353
4.000 0.8775 0.01396 0.00854 -0.0687 0.5349 0.9377
4.250 0.9032 0.01396 0.00855 -0.0686 0.5332 0.9398
4.500 0.9298 0.01393 0.00855 -0.0688 0.5315 0.9419
4.750 0.9578 0.01390 0.00851 -0.0692 0.5301 0.9438
5.000 0.9872 0.01386 0.00846 -0.0700 0.5287 0.9454
5.250 1.0175 0.01385 0.00843 -0.0710 0.5274 0.9466
5.500 1.0440 0.01386 0.00843 -0.0710 0.5258 0.9484
5.750 1.0625 0.01385 0.00854 -0.0696 0.5234 0.9514
6.000 1.0855 0.01385 0.00861 -0.0692 0.5209 0.9536
6.250 1.1112 0.01381 0.00863 -0.0692 0.5186 0.9554
6.500 1.1390 0.01375 0.00859 -0.0697 0.5166 0.9567
6.750 1.1684 0.01369 0.00853 -0.0705 0.5148 0.9578
7.000 1.1997 0.01350 0.00831 -0.0715 0.5123 0.9588
7.250 1.2192 0.01338 0.00833 -0.0705 0.5076 0.9608
7.500 1.2440 0.01295 0.00791 -0.0702 0.5018 0.9623
7.750 1.2703 0.01271 0.00766 -0.0702 0.4973 0.9637
8.000 1.2902 0.01265 0.00773 -0.0693 0.4912 0.9657
8.250 1.3135 0.01242 0.00748 -0.0688 0.4837 0.9676
8.500 1.3311 0.01235 0.00747 -0.0674 0.4722 0.9706
8.750 1.3465 0.01238 0.00750 -0.0657 0.4572 0.9733
9.000 1.3568 0.01262 0.00772 -0.0632 0.4363 0.9773
9.250 1.3605 0.01330 0.00830 -0.0601 0.4096 0.9831
9.500 1.3575 0.01483 0.00968 -0.0575 0.3759 1.0000
9.750 1.3419 0.01721 0.01196 -0.0542 0.3506 1.0000
10.000 1.3323 0.02007 0.01481 -0.0529 0.3337 1.0000
10.250 1.3175 0.02371 0.01841 -0.0518 0.3160 1.0000
10.500 1.3028 0.02728 0.02195 -0.0505 0.2981 1.0000
10.750 1.2800 0.03136 0.02594 -0.0486 0.2724 1.0000
11.000 1.2647 0.03479 0.02930 -0.0470 0.2498 1.0000
11.250 1.2269 0.04009 0.03437 -0.0444 0.2109 1.0000
11.500 1.1980 0.04504 0.03910 -0.0426 0.1726 1.0000
11.750 1.1716 0.05000 0.04381 -0.0411 0.1275 1.0000
12.000 1.1527 0.05449 0.04808 -0.0402 0.0871 1.0000
12.250 1.1292 0.05967 0.05301 -0.0393 0.0415 1.0000
12.500 1.1233 0.06325 0.05650 -0.0392 0.0183 1.0000
12.750 1.1247 0.06612 0.05936 -0.0392 0.0130 1.0000
13.000 1.1296 0.06866 0.06197 -0.0394 0.0119 1.0000
13.250 1.1346 0.07122 0.06461 -0.0396 0.0109 1.0000
13.500 1.1410 0.07367 0.06713 -0.0399 0.0105 1.0000
13.750 1.1451 0.07643 0.06998 -0.0402 0.0100 1.0000
14.000 1.1504 0.07904 0.07266 -0.0406 0.0097 1.0000
14.250 1.1533 0.08201 0.07571 -0.0410 0.0094 1.0000
14.500 1.1559 0.08505 0.07883 -0.0414 0.0092 1.0000
14.750 1.1581 0.08820 0.08206 -0.0420 0.0090 1.0000
15.000 1.1580 0.09170 0.08563 -0.0426 0.0088 1.0000
15.250 1.1572 0.09532 0.08934 -0.0433 0.0086 1.0000
15.500 1.1559 0.09905 0.09316 -0.0440 0.0084 1.0000
15.750 1.1568 0.10254 0.09672 -0.0448 0.0084 1.0000
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