WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 08-S-176 AIRFOIL (fx08s176-il) Reynolds number: 200,000 Max Cl/Cd: 50.76 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx08s176-il-200000-n5.txt Download as CSV file: xf-fx08s176-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0931 0.10275 0.09713 -0.0855 0.6051 0.0162
-11.000 -0.0891 0.09940 0.09380 -0.0868 0.6042 0.0160
-10.750 -0.0918 0.09437 0.08881 -0.0893 0.6034 0.0164
-10.500 -0.0877 0.09167 0.08617 -0.0903 0.6024 0.0170
-10.250 -0.0752 0.09076 0.08526 -0.0905 0.6011 0.0183
-10.000 -0.0754 0.08687 0.08141 -0.0923 0.6003 0.0183
-9.750 -0.0738 0.08352 0.07809 -0.0940 0.5994 0.0193
-9.500 -0.0774 0.07911 0.07373 -0.0963 0.5986 0.0190
-9.250 -0.0855 0.07386 0.06854 -0.0994 0.5979 0.0185
-9.000 -0.0988 0.06782 0.06255 -0.1041 0.5971 0.0183
-8.750 -0.1231 0.06150 0.05621 -0.1070 0.5965 0.0178
-8.500 -0.1450 0.05737 0.05202 -0.1061 0.5958 0.0177
-8.250 -0.1691 0.05229 0.04677 -0.1040 0.5951 0.0173
-8.000 -0.1778 0.04839 0.04268 -0.1021 0.5943 0.0174
-7.750 -0.1783 0.04535 0.03944 -0.1004 0.5935 0.0177
-7.500 -0.1764 0.04217 0.03600 -0.0985 0.5927 0.0180
-7.250 -0.1707 0.03926 0.03280 -0.0966 0.5919 0.0185
-7.000 -0.1623 0.03633 0.02952 -0.0948 0.5910 0.0193
-6.750 -0.1517 0.03329 0.02601 -0.0928 0.5902 0.0208
-6.500 -0.1385 0.03041 0.02262 -0.0909 0.5890 0.0218
-6.250 -0.1205 0.02846 0.02026 -0.0895 0.5877 0.0224
-6.000 -0.1009 0.02656 0.01812 -0.0887 0.5866 0.0232
-5.750 -0.0782 0.02581 0.01730 -0.0883 0.5854 0.0243
-5.500 -0.0546 0.02518 0.01655 -0.0879 0.5843 0.0258
-5.250 -0.0303 0.02422 0.01539 -0.0875 0.5831 0.0270
-5.000 -0.0052 0.02324 0.01421 -0.0870 0.5820 0.0279
-4.750 0.0202 0.02242 0.01324 -0.0867 0.5810 0.0287
-4.500 0.0458 0.02183 0.01250 -0.0864 0.5798 0.0296
-4.250 0.0701 0.02105 0.01169 -0.0860 0.5787 0.0316
-4.000 0.0951 0.02058 0.01117 -0.0857 0.5777 0.0330
-3.750 0.1199 0.02012 0.01065 -0.0853 0.5768 0.0342
-3.500 0.1446 0.01973 0.01019 -0.0849 0.5760 0.0357
-3.250 0.1687 0.01943 0.00983 -0.0845 0.5751 0.0373
-3.000 0.1917 0.01920 0.00960 -0.0839 0.5738 0.0391
-2.750 0.2150 0.01901 0.00945 -0.0834 0.5724 0.0429
-2.500 0.2392 0.01891 0.00935 -0.0831 0.5710 0.0485
-2.250 0.2632 0.01873 0.00920 -0.0827 0.5695 0.0571
-2.000 0.2878 0.01856 0.00904 -0.0824 0.5680 0.0719
-1.750 0.3127 0.01842 0.00892 -0.0822 0.5667 0.0902
-1.250 0.3473 0.01635 0.00879 -0.0801 0.5646 0.6072
-1.000 0.3551 0.01667 0.00979 -0.0741 0.5637 0.7862
-0.750 0.3777 0.01709 0.01011 -0.0727 0.5628 0.8327
-0.500 0.3977 0.01753 0.01048 -0.0703 0.5618 0.8556
-0.250 0.4196 0.01782 0.01067 -0.0686 0.5609 0.8698
0.000 0.4379 0.01816 0.01102 -0.0668 0.5592 0.8803
0.250 0.4581 0.01844 0.01129 -0.0655 0.5573 0.8873
0.500 0.4798 0.01864 0.01146 -0.0647 0.5553 0.8925
0.750 0.5005 0.01882 0.01162 -0.0633 0.5536 0.8999
1.000 0.5213 0.01896 0.01172 -0.0619 0.5521 0.9083
1.250 0.5438 0.01906 0.01177 -0.0609 0.5507 0.9158
1.500 0.5689 0.01905 0.01169 -0.0606 0.5494 0.9199
1.750 0.5976 0.01893 0.01148 -0.0610 0.5479 0.9219
2.000 0.6273 0.01879 0.01124 -0.0615 0.5466 0.9240
2.250 0.6418 0.01907 0.01161 -0.0597 0.5427 0.9282
2.500 0.6613 0.01919 0.01174 -0.0586 0.5397 0.9322
2.750 0.6856 0.01924 0.01178 -0.0583 0.5378 0.9350
3.000 0.7112 0.01928 0.01180 -0.0582 0.5363 0.9378
3.250 0.7375 0.01926 0.01176 -0.0583 0.5349 0.9407
3.500 0.7638 0.01923 0.01168 -0.0583 0.5337 0.9439
3.750 0.7912 0.01917 0.01158 -0.0586 0.5326 0.9466
4.000 0.8078 0.01957 0.01209 -0.0573 0.5295 0.9497
4.250 0.8245 0.01993 0.01254 -0.0561 0.5263 0.9533
4.500 0.8460 0.02010 0.01274 -0.0556 0.5241 0.9563
4.750 0.8700 0.02016 0.01281 -0.0554 0.5223 0.9584
5.000 0.8961 0.02016 0.01282 -0.0556 0.5208 0.9601
5.250 0.9257 0.02011 0.01277 -0.0564 0.5196 0.9614
5.500 0.9568 0.02003 0.01268 -0.0574 0.5185 0.9628
5.750 0.9597 0.02095 0.01381 -0.0545 0.5132 0.9676
6.000 0.9782 0.02122 0.01414 -0.0538 0.5101 0.9705
6.500 1.0335 0.02114 0.01413 -0.0548 0.5064 0.9744
6.750 1.0660 0.02100 0.01402 -0.0561 0.5051 0.9759
7.000 1.0617 0.02231 0.01553 -0.0528 0.4990 0.9835
7.250 1.0809 0.02275 0.01606 -0.0527 0.4956 0.9881
7.500 1.1083 0.02276 0.01612 -0.0534 0.4935 0.9928
7.750 1.1383 0.02257 0.01599 -0.0542 0.4920 1.0000
8.250 1.1150 0.02615 0.01978 -0.0480 0.4794 1.0000
8.500 1.1478 0.02573 0.01941 -0.0488 0.4781 1.0000
8.750 1.0870 0.03271 0.02648 -0.0456 0.4606 1.0000
9.250 1.1303 0.03334 0.02721 -0.0461 0.4510 1.0000
9.750 1.1405 0.03666 0.03056 -0.0451 0.4262 1.0000
10.000 1.1698 0.03622 0.03016 -0.0455 0.4197 1.0000
10.250 1.1831 0.03722 0.03119 -0.0453 0.4109 1.0000
10.500 1.2117 0.03659 0.03045 -0.0454 0.3938 1.0000
10.750 1.2152 0.03823 0.03197 -0.0445 0.3721 1.0000
11.000 1.2221 0.03957 0.03320 -0.0438 0.3541 1.0000
11.250 1.2216 0.04160 0.03511 -0.0427 0.3349 1.0000
11.500 1.2255 0.04349 0.03702 -0.0422 0.3234 1.0000
11.750 1.2210 0.04621 0.03967 -0.0413 0.3021 1.0000
12.000 1.2154 0.04914 0.04251 -0.0406 0.2769 1.0000
12.250 1.1942 0.05363 0.04669 -0.0395 0.2295 1.0000
12.500 1.1606 0.05965 0.05233 -0.0383 0.1794 1.0000
12.750 1.1377 0.06490 0.05733 -0.0377 0.1357 1.0000
13.000 1.1139 0.07047 0.06261 -0.0374 0.0888 1.0000
13.250 1.0920 0.07606 0.06792 -0.0373 0.0449 1.0000
13.500 1.0844 0.08016 0.07190 -0.0375 0.0182 1.0000
13.750 1.0836 0.08354 0.07529 -0.0379 0.0135 1.0000
14.000 1.0863 0.08655 0.07836 -0.0383 0.0117 1.0000
14.250 1.0905 0.08941 0.08132 -0.0388 0.0110 1.0000
14.500 1.0941 0.09235 0.08437 -0.0393 0.0103 1.0000
14.750 1.0972 0.09543 0.08756 -0.0399 0.0098 1.0000
15.000 1.1002 0.09853 0.09079 -0.0405 0.0095 1.0000
15.250 1.1033 0.10167 0.09406 -0.0413 0.0093 1.0000
15.500 1.1067 0.10478 0.09729 -0.0420 0.0091 1.0000
15.750 1.1092 0.10804 0.10067 -0.0429 0.0089 1.0000
16.000 1.1117 0.11132 0.10407 -0.0438 0.0088 1.0000
16.250 1.1137 0.11471 0.10757 -0.0447 0.0086 1.0000
16.500 1.1157 0.11811 0.11108 -0.0458 0.0084 1.0000
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