74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il) Reynolds number: 100,000 Max Cl/Cd: 44.98 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx74130wp2mod-il-100000-n5.txt Download as CSV file: xf-fx74130wp2mod-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: 74-130 WP2 MOD
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1758 0.09745 0.09234 -0.0953 0.9177 0.0480
-9.750 -0.1718 0.09397 0.08887 -0.0983 0.9141 0.0494
-9.500 -0.1769 0.09080 0.08574 -0.1041 0.9086 0.0514
-9.250 -0.1791 0.08684 0.08180 -0.1094 0.9039 0.0518
-9.000 -0.1844 0.08285 0.07781 -0.1139 0.8988 0.0519
-8.500 -0.1011 0.06193 0.05707 -0.1063 0.8850 0.0343
-8.000 -0.1318 0.05078 0.04580 -0.1148 0.8764 0.0269
-7.500 -0.1806 0.05876 0.05336 -0.1180 0.8759 0.0261
-7.250 -0.1809 0.05589 0.05036 -0.1173 0.8719 0.0253
-7.000 -0.1806 0.05310 0.04743 -0.1162 0.8671 0.0247
-6.750 -0.1758 0.05004 0.04416 -0.1154 0.8631 0.0239
-6.500 -0.1690 0.04694 0.04078 -0.1144 0.8594 0.0232
-6.250 -0.1640 0.04432 0.03790 -0.1125 0.8540 0.0225
-6.000 -0.1527 0.04140 0.03463 -0.1112 0.8501 0.0218
-5.750 -0.1368 0.03850 0.03131 -0.1101 0.8472 0.0217
-5.500 -0.1256 0.03666 0.02916 -0.1081 0.8422 0.0219
-5.250 -0.1085 0.03491 0.02707 -0.1068 0.8382 0.0234
-5.000 -0.0867 0.03296 0.02468 -0.1060 0.8352 0.0248
-4.750 -0.0626 0.03098 0.02228 -0.1054 0.8328 0.0250
-4.500 -0.0470 0.02969 0.02070 -0.1033 0.8275 0.0251
-4.250 -0.0234 0.02818 0.01886 -0.1024 0.8240 0.0254
-4.000 0.0033 0.02680 0.01722 -0.1020 0.8214 0.0258
-3.750 0.0315 0.02556 0.01576 -0.1017 0.8194 0.0265
-3.500 0.0464 0.02502 0.01514 -0.0995 0.8135 0.0273
-3.250 0.0682 0.02399 0.01408 -0.0985 0.8099 0.0287
-3.000 0.0931 0.02325 0.01330 -0.0982 0.8072 0.0328
-2.750 0.1145 0.02289 0.01279 -0.0971 0.8034 0.0387
-2.500 0.1318 0.02246 0.01233 -0.0955 0.7981 0.0456
-2.250 0.1556 0.02171 0.01174 -0.0947 0.7948 0.0854
-2.000 0.1604 0.01934 0.01183 -0.0905 0.7922 0.6288
-1.750 0.1562 0.02020 0.01298 -0.0826 0.7846 0.8094
-1.500 0.1576 0.02072 0.01352 -0.0742 0.7808 0.8826
-1.250 0.2156 0.02098 0.01350 -0.0770 0.7804 0.9384
-1.000 0.2549 0.02089 0.01316 -0.0793 0.7786 0.9460
-0.750 0.2809 0.02113 0.01327 -0.0798 0.7723 0.9525
-0.500 0.3085 0.02114 0.01311 -0.0802 0.7684 0.9580
-0.250 0.3472 0.02104 0.01285 -0.0827 0.7661 0.9605
0.000 0.3841 0.02093 0.01260 -0.0848 0.7643 0.9631
0.250 0.3987 0.02139 0.01302 -0.0834 0.7562 0.9693
0.500 0.4304 0.02136 0.01290 -0.0846 0.7532 0.9721
0.750 0.4658 0.02126 0.01271 -0.0864 0.7512 0.9741
1.000 0.4846 0.02171 0.01315 -0.0859 0.7434 0.9791
1.250 0.5127 0.02175 0.01315 -0.0865 0.7400 0.9823
1.500 0.5450 0.02170 0.01305 -0.0877 0.7378 0.9847
1.750 0.5636 0.02226 0.01364 -0.0873 0.7303 0.9896
2.000 0.5914 0.02235 0.01372 -0.0879 0.7266 0.9931
2.250 0.6229 0.02228 0.01366 -0.0889 0.7243 0.9957
2.500 0.6273 0.02299 0.01441 -0.0859 0.7157 1.0000
2.750 0.6423 0.02308 0.01451 -0.0839 0.7121 1.0000
3.000 0.6550 0.02323 0.01467 -0.0815 0.7082 1.0000
3.250 0.6431 0.02389 0.01535 -0.0753 0.6992 1.0000
3.500 0.6676 0.02382 0.01531 -0.0749 0.6970 1.0000
3.750 0.6587 0.02488 0.01642 -0.0699 0.6871 1.0000
4.000 0.6863 0.02490 0.01648 -0.0702 0.6848 1.0000
4.250 0.7173 0.02482 0.01646 -0.0709 0.6831 1.0000
4.500 0.7151 0.02616 0.01783 -0.0676 0.6729 1.0000
4.750 0.7456 0.02609 0.01784 -0.0682 0.6709 1.0000
5.000 0.7774 0.02596 0.01785 -0.0689 0.6692 1.0000
5.250 0.7822 0.02714 0.01909 -0.0667 0.6587 1.0000
5.500 0.8165 0.02669 0.01875 -0.0675 0.6569 1.0000
6.000 0.8565 0.02750 0.01979 -0.0662 0.6444 1.0000
6.250 0.8935 0.02675 0.01923 -0.0670 0.6420 1.0000
6.500 0.9057 0.02739 0.01999 -0.0654 0.6314 1.0000
7.000 0.9737 0.02552 0.01850 -0.0655 0.6161 1.0000
7.250 1.0000 0.02493 0.01806 -0.0647 0.6029 1.0000
7.500 1.0268 0.02416 0.01742 -0.0637 0.5844 1.0000
7.750 1.0534 0.02342 0.01676 -0.0625 0.5585 1.0000
8.000 1.0652 0.02378 0.01718 -0.0603 0.5291 1.0000
8.250 1.0728 0.02443 0.01783 -0.0576 0.4880 1.0000
8.500 1.0825 0.02483 0.01782 -0.0547 0.3916 1.0000
8.750 1.0752 0.02671 0.01903 -0.0507 0.3043 1.0000
9.000 1.0654 0.02911 0.02097 -0.0472 0.2360 1.0000
9.250 1.0596 0.03142 0.02294 -0.0445 0.1790 1.0000
9.500 1.0574 0.03362 0.02484 -0.0421 0.1314 1.0000
9.750 1.0578 0.03574 0.02670 -0.0401 0.0941 1.0000
10.000 1.0610 0.03771 0.02852 -0.0384 0.0709 1.0000
10.250 1.0655 0.03965 0.03043 -0.0368 0.0580 1.0000
10.500 1.0709 0.04155 0.03236 -0.0353 0.0486 1.0000
10.750 1.0746 0.04367 0.03448 -0.0339 0.0420 1.0000
11.000 1.0819 0.04552 0.03647 -0.0327 0.0359 1.0000
11.250 1.0855 0.04776 0.03873 -0.0314 0.0315 1.0000
11.500 1.0935 0.04973 0.04093 -0.0302 0.0278 1.0000
11.750 1.1004 0.05177 0.04305 -0.0293 0.0245 1.0000
12.000 1.1077 0.05398 0.04534 -0.0283 0.0219 1.0000
12.250 1.1204 0.05590 0.04746 -0.0273 0.0200 1.0000
12.500 1.1343 0.05793 0.04967 -0.0263 0.0185 1.0000
12.750 1.1468 0.06011 0.05201 -0.0255 0.0174 1.0000
13.000 1.1545 0.06257 0.05459 -0.0250 0.0161 1.0000
13.250 1.1635 0.06567 0.05785 -0.0243 0.0150 1.0000
13.500 1.1680 0.06861 0.06115 -0.0237 0.0142 1.0000
13.750 1.1697 0.07203 0.06490 -0.0232 0.0135 1.0000
14.000 1.1683 0.07591 0.06911 -0.0228 0.0132 1.0000
14.250 1.1628 0.08026 0.07377 -0.0227 0.0130 1.0000
14.500 1.1538 0.08502 0.07885 -0.0230 0.0128 1.0000
14.750 1.1421 0.09023 0.08435 -0.0237 0.0128 1.0000
15.000 1.1279 0.09596 0.09036 -0.0251 0.0127 1.0000
15.250 1.1128 0.10204 0.09671 -0.0271 0.0127 1.0000
15.500 1.0955 0.10880 0.10372 -0.0298 0.0127 1.0000
15.750 1.0776 0.11608 0.11124 -0.0333 0.0128 1.0000
16.000 1.0586 0.12417 0.11953 -0.0377 0.0129 1.0000
16.250 1.0389 0.13316 0.12871 -0.0431 0.0131 1.0000
16.500 1.0191 0.14320 0.13889 -0.0496 0.0133 1.0000
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Polar data table (+)
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