GOE 632 AIRFOIL (goe632-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 632 AIRFOIL (goe632-il) Reynolds number: 50,000 Max Cl/Cd: 26 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe632-il-50000-n5.txt Download as CSV file: xf-goe632-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 632 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3444 0.09707 0.09042 -0.0446 1.0000 0.0960
-8.750 -0.3564 0.09490 0.08837 -0.0425 1.0000 0.0938
-8.500 -0.4306 0.09155 0.08515 -0.0422 0.9986 0.0850
-8.250 -0.4144 0.08723 0.08081 -0.0453 0.9886 0.0841
-8.000 -0.4048 0.08268 0.07618 -0.0489 0.9767 0.0834
-7.750 -0.3974 0.07795 0.07133 -0.0524 0.9640 0.0829
-7.500 -0.3901 0.07345 0.06670 -0.0550 0.9520 0.0821
-7.250 -0.3806 0.06893 0.06199 -0.0575 0.9417 0.0810
-7.000 -0.3768 0.06497 0.05781 -0.0580 0.9290 0.0797
-6.750 -0.3713 0.06110 0.05366 -0.0580 0.9175 0.0786
-6.500 -0.3584 0.05698 0.04916 -0.0589 0.9092 0.0777
-6.250 -0.3528 0.05396 0.04578 -0.0573 0.8973 0.0771
-6.000 -0.3379 0.05101 0.04246 -0.0568 0.8889 0.0774
-5.750 -0.3220 0.04868 0.03981 -0.0560 0.8797 0.0786
-5.500 -0.3055 0.04644 0.03720 -0.0549 0.8711 0.0798
-5.250 -0.2872 0.04428 0.03465 -0.0539 0.8628 0.0809
-5.000 -0.2686 0.04232 0.03228 -0.0526 0.8545 0.0814
-4.750 -0.2471 0.04045 0.03001 -0.0517 0.8465 0.0820
-4.500 -0.2219 0.03872 0.02787 -0.0512 0.8397 0.0828
-4.250 -0.2003 0.03736 0.02613 -0.0500 0.8309 0.0840
-4.000 -0.1655 0.03574 0.02420 -0.0512 0.8260 0.0867
-3.750 -0.1473 0.03495 0.02335 -0.0497 0.8159 0.0895
-3.500 -0.1102 0.03367 0.02186 -0.0512 0.8105 0.0927
-3.250 -0.0844 0.03285 0.02083 -0.0507 0.8018 0.0951
-3.000 -0.0448 0.03180 0.01952 -0.0524 0.7955 0.0989
-2.750 0.0018 0.03069 0.01842 -0.0558 0.7903 0.1069
-2.500 0.0351 0.03019 0.01776 -0.0568 0.7813 0.1140
-2.250 0.0810 0.02921 0.01678 -0.0599 0.7761 0.1263
-2.000 0.1044 0.02887 0.01648 -0.0593 0.7666 0.1394
-1.750 0.1391 0.02812 0.01582 -0.0604 0.7603 0.1643
-1.500 0.3950 0.02482 0.01497 -0.1008 0.7624 1.0000
-1.250 0.4160 0.02496 0.01488 -0.0997 0.7532 1.0000
-1.000 0.4378 0.02507 0.01478 -0.0986 0.7443 1.0000
-0.750 0.4563 0.02531 0.01485 -0.0970 0.7347 1.0000
-0.500 0.4796 0.02537 0.01473 -0.0961 0.7267 1.0000
-0.250 0.4963 0.02569 0.01492 -0.0943 0.7169 1.0000
0.000 0.5208 0.02571 0.01478 -0.0935 0.7094 1.0000
0.250 0.5360 0.02610 0.01508 -0.0915 0.6995 1.0000
0.500 0.5611 0.02611 0.01494 -0.0908 0.6926 1.0000
0.750 0.5753 0.02655 0.01532 -0.0886 0.6826 1.0000
1.000 0.6005 0.02656 0.01521 -0.0879 0.6759 1.0000
1.250 0.6138 0.02707 0.01568 -0.0856 0.6663 1.0000
1.500 0.6383 0.02713 0.01563 -0.0848 0.6596 1.0000
1.750 0.6514 0.02767 0.01614 -0.0824 0.6502 1.0000
2.000 0.6746 0.02780 0.01619 -0.0814 0.6435 1.0000
2.250 0.6883 0.02834 0.01672 -0.0792 0.6348 1.0000
2.500 0.7087 0.02861 0.01694 -0.0778 0.6276 1.0000
2.750 0.7258 0.02904 0.01734 -0.0760 0.6201 1.0000
3.000 0.7405 0.02956 0.01786 -0.0739 0.6120 1.0000
3.250 0.7686 0.02956 0.01778 -0.0736 0.6070 1.0000
3.500 0.7700 0.03066 0.01896 -0.0698 0.5970 1.0000
3.750 0.7947 0.03080 0.01906 -0.0690 0.5914 1.0000
4.000 0.7986 0.03184 0.02015 -0.0655 0.5827 1.0000
4.250 0.8167 0.03227 0.02060 -0.0639 0.5764 1.0000
4.500 0.8341 0.03276 0.02109 -0.0622 0.5703 1.0000
4.750 0.8353 0.03391 0.02229 -0.0584 0.5617 1.0000
5.000 0.8615 0.03403 0.02241 -0.0579 0.5571 1.0000
5.250 0.8518 0.03571 0.02417 -0.0528 0.5481 1.0000
5.500 0.8696 0.03618 0.02467 -0.0512 0.5424 1.0000
5.750 0.8806 0.03697 0.02550 -0.0487 0.5364 1.0000
6.000 0.8740 0.03851 0.02709 -0.0442 0.5278 1.0000
6.500 0.8751 0.04089 0.02953 -0.0369 0.5129 1.0000
6.750 0.9137 0.04018 0.02888 -0.0374 0.5079 1.0000
7.000 0.8733 0.04315 0.03186 -0.0292 0.4971 1.0000
7.250 0.9144 0.04215 0.03092 -0.0298 0.4921 1.0000
7.500 0.8787 0.04526 0.03404 -0.0231 0.4806 1.0000
7.750 0.9275 0.04344 0.03230 -0.0237 0.4756 1.0000
8.000 0.8947 0.04675 0.03563 -0.0181 0.4635 1.0000
8.250 0.9592 0.04349 0.03244 -0.0194 0.4585 1.0000
8.500 0.9211 0.04737 0.03635 -0.0139 0.4461 1.0000
8.750 0.9220 0.04876 0.03780 -0.0113 0.4364 1.0000
9.000 0.9546 0.04734 0.03646 -0.0100 0.4282 1.0000
9.250 0.9370 0.05036 0.03953 -0.0070 0.4161 1.0000
9.500 0.9818 0.04757 0.03679 -0.0059 0.4078 1.0000
9.750 0.9779 0.04930 0.03860 -0.0033 0.3959 1.0000
10.000 0.9673 0.05181 0.04117 -0.0010 0.3828 1.0000
10.250 0.9769 0.05242 0.04185 0.0009 0.3716 1.0000
10.500 1.0028 0.05135 0.04086 0.0026 0.3613 1.0000
10.750 0.9892 0.05447 0.04406 0.0044 0.3475 1.0000
11.000 0.9842 0.05688 0.04656 0.0059 0.3340 1.0000
11.250 0.9877 0.05837 0.04813 0.0073 0.3211 1.0000
11.500 0.9984 0.05902 0.04883 0.0088 0.3083 1.0000
11.750 1.0085 0.05974 0.04960 0.0103 0.2947 1.0000
12.000 1.0130 0.06120 0.05110 0.0115 0.2805 1.0000
12.250 1.0138 0.06318 0.05311 0.0126 0.2660 1.0000
12.500 1.0153 0.06521 0.05515 0.0136 0.2525 1.0000
12.750 1.0187 0.06704 0.05698 0.0145 0.2398 1.0000
13.000 1.0231 0.06885 0.05878 0.0154 0.2289 1.0000
13.250 1.0346 0.06975 0.05964 0.0166 0.2201 1.0000
13.500 1.0397 0.07165 0.06154 0.0174 0.2116 1.0000
13.750 1.0471 0.07332 0.06321 0.0182 0.2048 1.0000
14.000 1.0524 0.07536 0.06530 0.0188 0.1984 1.0000
14.250 1.0709 0.07560 0.06545 0.0201 0.1935 1.0000
14.500 1.0623 0.07984 0.06992 0.0199 0.1883 1.0000
14.750 1.0661 0.08231 0.07247 0.0202 0.1839 1.0000
15.000 1.0907 0.08179 0.07191 0.0216 0.1797 1.0000
15.250 1.0754 0.08717 0.07750 0.0208 0.1761 1.0000
15.500 1.0448 0.09520 0.08577 0.0186 0.1723 1.0000
15.750 1.0208 0.10261 0.09333 0.0165 0.1688 1.0000
16.000 1.0240 0.10553 0.09634 0.0163 0.1660 1.0000
16.250 1.0408 0.10622 0.09710 0.0172 0.1641 1.0000
16.500 0.8705 0.14555 0.13634 -0.0013 0.1570 1.0000
16.750 0.8614 0.15187 0.14268 -0.0038 0.1544 1.0000
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Polar data table (+)
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