GOE 704 AIRFOIL (goe704-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 704 AIRFOIL (goe704-il) Reynolds number: 100,000 Max Cl/Cd: 44.45 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe704-il-100000-n5.txt Download as CSV file: xf-goe704-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 704 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.8079 0.07022 0.06490 -0.0375 1.0000 0.0324
-12.500 -0.8380 0.06002 0.05449 -0.0466 1.0000 0.0320
-12.250 -0.8624 0.05393 0.04814 -0.0494 1.0000 0.0320
-12.000 -0.8820 0.04954 0.04346 -0.0491 1.0000 0.0323
-11.750 -0.8941 0.04639 0.04010 -0.0472 1.0000 0.0328
-11.500 -0.8982 0.04431 0.03794 -0.0448 1.0000 0.0336
-11.250 -0.8997 0.04238 0.03589 -0.0422 1.0000 0.0345
-11.000 -0.8974 0.04039 0.03375 -0.0400 1.0000 0.0358
-10.750 -0.8932 0.03833 0.03143 -0.0378 1.0000 0.0377
-10.500 -0.8871 0.03614 0.02889 -0.0357 1.0000 0.0399
-10.250 -0.8766 0.03481 0.02755 -0.0339 1.0000 0.0421
-10.000 -0.8646 0.03334 0.02593 -0.0321 1.0000 0.0450
-9.750 -0.8520 0.03164 0.02392 -0.0303 1.0000 0.0486
-9.500 -0.8377 0.03064 0.02294 -0.0287 1.0000 0.0523
-9.250 -0.8221 0.02942 0.02147 -0.0271 1.0000 0.0573
-9.000 -0.8067 0.02856 0.02061 -0.0254 1.0000 0.0617
-8.750 -0.7906 0.02776 0.01966 -0.0238 1.0000 0.0675
-8.500 -0.7760 0.02720 0.01908 -0.0218 1.0000 0.0725
-8.250 -0.7626 0.02674 0.01851 -0.0195 1.0000 0.0785
-8.000 -0.7483 0.02641 0.01814 -0.0176 0.9986 0.0841
-7.750 -0.7136 0.02579 0.01723 -0.0195 0.9896 0.0934
-7.500 -0.6788 0.02542 0.01684 -0.0215 0.9811 0.1007
-7.250 -0.6442 0.02468 0.01587 -0.0233 0.9730 0.1086
-7.000 -0.6116 0.02423 0.01532 -0.0247 0.9633 0.1161
-6.750 -0.5787 0.02359 0.01448 -0.0260 0.9544 0.1235
-6.500 -0.5457 0.02313 0.01392 -0.0273 0.9460 0.1310
-6.250 -0.5152 0.02257 0.01318 -0.0280 0.9362 0.1381
-6.000 -0.4832 0.02210 0.01265 -0.0290 0.9286 0.1451
-5.750 -0.4545 0.02166 0.01199 -0.0293 0.9185 0.1521
-5.500 -0.4251 0.02117 0.01152 -0.0297 0.9106 0.1584
-5.250 -0.3970 0.02079 0.01100 -0.0298 0.9016 0.1655
-5.000 -0.3692 0.02034 0.01053 -0.0299 0.8937 0.1719
-4.750 -0.3419 0.01998 0.01010 -0.0298 0.8854 0.1788
-4.500 -0.3146 0.01960 0.00966 -0.0296 0.8781 0.1853
-4.250 -0.2882 0.01926 0.00931 -0.0294 0.8702 0.1922
-4.000 -0.2610 0.01894 0.00892 -0.0291 0.8635 0.1994
-3.750 -0.2350 0.01861 0.00863 -0.0288 0.8558 0.2062
-3.500 -0.2077 0.01833 0.00830 -0.0286 0.8500 0.2153
-3.250 -0.1820 0.01808 0.00809 -0.0282 0.8421 0.2256
-3.000 -0.1556 0.01781 0.00785 -0.0278 0.8360 0.2375
-2.750 -0.1295 0.01758 0.00765 -0.0275 0.8291 0.2520
-2.500 -0.1032 0.01734 0.00748 -0.0271 0.8224 0.2713
-2.250 -0.0766 0.01709 0.00732 -0.0268 0.8166 0.2982
-2.000 -0.0506 0.01685 0.00722 -0.0265 0.8091 0.3334
-1.750 -0.0244 0.01653 0.00707 -0.0260 0.8032 0.3800
-1.500 0.0001 0.01616 0.00699 -0.0254 0.7954 0.4452
-1.250 0.0812 0.01546 0.00785 -0.0338 0.7899 0.8426
-1.000 0.0995 0.01572 0.00800 -0.0311 0.7806 0.8937
-0.750 0.1306 0.01597 0.00812 -0.0308 0.7714 0.9232
-0.500 0.1677 0.01622 0.00827 -0.0321 0.7611 0.9453
-0.250 0.2166 0.01636 0.00827 -0.0359 0.7528 0.9624
0.000 0.2689 0.01644 0.00828 -0.0407 0.7430 0.9790
0.250 0.3392 0.01632 0.00806 -0.0494 0.7334 1.0000
0.500 0.3636 0.01629 0.00796 -0.0487 0.7240 1.0000
0.750 0.3884 0.01628 0.00791 -0.0482 0.7134 1.0000
1.000 0.4128 0.01626 0.00782 -0.0474 0.7033 1.0000
1.250 0.4372 0.01623 0.00774 -0.0467 0.6919 1.0000
1.500 0.4616 0.01622 0.00771 -0.0461 0.6791 1.0000
1.750 0.4859 0.01620 0.00766 -0.0453 0.6656 1.0000
2.000 0.5101 0.01618 0.00760 -0.0445 0.6513 1.0000
2.250 0.5343 0.01617 0.00756 -0.0438 0.6360 1.0000
2.500 0.5584 0.01616 0.00754 -0.0430 0.6195 1.0000
2.750 0.5824 0.01617 0.00753 -0.0422 0.6020 1.0000
3.000 0.6062 0.01619 0.00751 -0.0413 0.5833 1.0000
3.250 0.6298 0.01624 0.00752 -0.0405 0.5627 1.0000
3.500 0.6531 0.01632 0.00754 -0.0396 0.5398 1.0000
3.750 0.6761 0.01644 0.00759 -0.0386 0.5162 1.0000
4.000 0.6986 0.01662 0.00767 -0.0375 0.4910 1.0000
4.250 0.7207 0.01686 0.00779 -0.0365 0.4658 1.0000
4.500 0.7422 0.01716 0.00796 -0.0354 0.4420 1.0000
4.750 0.7635 0.01749 0.00821 -0.0343 0.4193 1.0000
5.000 0.7843 0.01786 0.00849 -0.0331 0.3986 1.0000
5.250 0.8048 0.01826 0.00880 -0.0319 0.3803 1.0000
5.500 0.8251 0.01867 0.00915 -0.0307 0.3638 1.0000
5.750 0.8452 0.01908 0.00952 -0.0294 0.3489 1.0000
6.000 0.8652 0.01949 0.00992 -0.0282 0.3353 1.0000
6.250 0.8849 0.01991 0.01033 -0.0269 0.3232 1.0000
6.500 0.9042 0.02036 0.01078 -0.0255 0.3127 1.0000
6.750 0.9232 0.02081 0.01123 -0.0241 0.3024 1.0000
7.000 0.9421 0.02124 0.01171 -0.0227 0.2922 1.0000
7.250 0.9601 0.02172 0.01217 -0.0211 0.2831 1.0000
7.500 0.9781 0.02217 0.01270 -0.0196 0.2734 1.0000
7.750 0.9956 0.02265 0.01322 -0.0179 0.2648 1.0000
8.000 1.0125 0.02314 0.01375 -0.0162 0.2568 1.0000
8.250 1.0296 0.02364 0.01432 -0.0146 0.2493 1.0000
8.500 1.0459 0.02415 0.01490 -0.0128 0.2423 1.0000
8.750 1.0623 0.02469 0.01553 -0.0110 0.2359 1.0000
9.000 1.0780 0.02523 0.01617 -0.0092 0.2291 1.0000
9.250 1.0929 0.02582 0.01680 -0.0072 0.2231 1.0000
9.500 1.1067 0.02639 0.01751 -0.0051 0.2153 1.0000
9.750 1.1183 0.02699 0.01815 -0.0028 0.2073 1.0000
10.000 1.1276 0.02759 0.01884 -0.0002 0.1976 1.0000
10.250 1.1356 0.02823 0.01960 0.0026 0.1868 1.0000
10.500 1.1409 0.02895 0.02034 0.0056 0.1768 1.0000
10.750 1.1438 0.02973 0.02117 0.0089 0.1669 1.0000
11.000 1.1491 0.03059 0.02214 0.0115 0.1559 1.0000
11.250 1.1543 0.03160 0.02323 0.0138 0.1452 1.0000
11.500 1.1594 0.03276 0.02446 0.0158 0.1331 1.0000
11.750 1.1638 0.03411 0.02585 0.0175 0.1184 1.0000
12.000 1.1653 0.03578 0.02753 0.0191 0.1040 1.0000
12.250 1.1645 0.03781 0.02953 0.0205 0.0931 1.0000
12.500 1.1618 0.04018 0.03189 0.0217 0.0838 1.0000
12.750 1.1557 0.04300 0.03472 0.0227 0.0752 1.0000
13.250 1.1486 0.04872 0.04067 0.0237 0.0517 1.0000
13.500 1.1392 0.05241 0.04438 0.0237 0.0448 1.0000
13.750 1.1282 0.05649 0.04853 0.0233 0.0410 1.0000
14.000 1.1155 0.06100 0.05314 0.0225 0.0386 1.0000
14.250 1.1006 0.06611 0.05835 0.0211 0.0371 1.0000
14.500 1.0852 0.07163 0.06399 0.0193 0.0361 1.0000
14.750 1.0704 0.07740 0.06992 0.0172 0.0352 1.0000
15.000 1.0554 0.08342 0.07609 0.0148 0.0343 1.0000
15.250 1.0411 0.08952 0.08233 0.0124 0.0336 1.0000
15.500 1.0276 0.09558 0.08851 0.0099 0.0328 1.0000
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