GOE 286 AIRFOIL (goe286-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 286 AIRFOIL (goe286-il) Reynolds number: 100,000 Max Cl/Cd: 52.25 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe286-il-100000.txt Download as CSV file: xf-goe286-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 286 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3723 0.09993 0.09517 -0.0163 1.0000 0.0836
-8.000 -0.3812 0.09847 0.09381 -0.0223 1.0000 0.0856
-7.750 -0.3838 0.09655 0.09189 -0.0348 1.0000 0.0864
-7.500 -0.3705 0.09013 0.08557 -0.0258 1.0000 0.0882
-7.250 -0.3581 0.08684 0.08231 -0.0227 1.0000 0.0914
-7.000 -0.3514 0.08386 0.07937 -0.0242 1.0000 0.0950
-6.750 -0.3481 0.08108 0.07662 -0.0300 1.0000 0.0995
-6.500 -0.3478 0.07813 0.07356 -0.0388 1.0000 0.1019
-6.250 -0.3419 0.07414 0.06972 -0.0337 1.0000 0.1034
-6.000 -0.3368 0.07152 0.06717 -0.0309 1.0000 0.1057
-5.750 -0.3325 0.06910 0.06478 -0.0301 1.0000 0.1092
-5.250 -0.3207 0.06329 0.05880 -0.0349 1.0000 0.1185
-5.000 -0.3176 0.06099 0.05661 -0.0318 1.0000 0.1210
-4.750 -0.3119 0.05906 0.05470 -0.0307 1.0000 0.1266
-4.500 -0.3013 0.05635 0.05182 -0.0334 1.0000 0.1346
-4.250 -0.2577 0.05291 0.04809 -0.0408 0.9935 0.1491
-4.000 -0.2187 0.04894 0.04421 -0.0444 0.9852 0.1573
-3.750 -0.1679 0.04539 0.04032 -0.0526 0.9754 0.1809
-3.500 -0.1266 0.04206 0.03699 -0.0567 0.9666 0.1998
-3.250 -0.0824 0.03927 0.03416 -0.0613 0.9584 0.2333
-2.500 0.0890 0.02738 0.01992 -0.0777 0.9304 0.1127
-2.250 0.1292 0.02522 0.01737 -0.0794 0.9174 0.1077
-2.000 0.1688 0.02388 0.01544 -0.0801 0.9038 0.1009
-1.750 0.2031 0.02223 0.01360 -0.0806 0.8897 0.0996
-1.500 0.2351 0.02099 0.01217 -0.0804 0.8749 0.0995
-1.250 0.2650 0.01999 0.01101 -0.0796 0.8596 0.1003
-1.000 0.2925 0.01896 0.00994 -0.0786 0.8433 0.1041
-0.750 0.3184 0.01824 0.00923 -0.0772 0.8260 0.1104
-0.500 0.3438 0.01763 0.00852 -0.0755 0.8081 0.1159
-0.250 0.3681 0.01693 0.00786 -0.0739 0.7900 0.1254
0.000 0.3929 0.01641 0.00733 -0.0724 0.7687 0.1483
0.250 0.4248 0.01354 0.00658 -0.0719 0.7487 1.0000
0.500 0.4500 0.01360 0.00631 -0.0706 0.7286 1.0000
0.750 0.4753 0.01370 0.00616 -0.0695 0.7065 1.0000
1.000 0.5007 0.01382 0.00602 -0.0685 0.6857 1.0000
1.250 0.5263 0.01401 0.00594 -0.0675 0.6659 1.0000
1.500 0.5521 0.01428 0.00600 -0.0667 0.6446 1.0000
1.750 0.5780 0.01459 0.00609 -0.0660 0.6249 1.0000
2.000 0.6041 0.01494 0.00623 -0.0654 0.6069 1.0000
2.250 0.6305 0.01529 0.00643 -0.0649 0.5902 1.0000
2.500 0.6569 0.01563 0.00665 -0.0645 0.5744 1.0000
2.750 0.6835 0.01595 0.00687 -0.0642 0.5594 1.0000
3.000 0.7100 0.01625 0.00711 -0.0639 0.5453 1.0000
3.250 0.7366 0.01654 0.00734 -0.0636 0.5322 1.0000
3.500 0.7632 0.01683 0.00756 -0.0633 0.5200 1.0000
3.750 0.7898 0.01710 0.00773 -0.0629 0.5090 1.0000
4.000 0.8164 0.01738 0.00799 -0.0626 0.4976 1.0000
4.250 0.8428 0.01771 0.00832 -0.0624 0.4870 1.0000
4.500 0.8694 0.01804 0.00859 -0.0621 0.4778 1.0000
4.750 0.8958 0.01838 0.00894 -0.0618 0.4681 1.0000
5.000 0.9219 0.01875 0.00932 -0.0615 0.4579 1.0000
5.250 0.9480 0.01908 0.00958 -0.0612 0.4479 1.0000
5.500 0.9736 0.01938 0.00988 -0.0607 0.4362 1.0000
5.750 0.9986 0.01971 0.01024 -0.0603 0.4238 1.0000
6.000 1.0240 0.02010 0.01066 -0.0599 0.4133 1.0000
6.250 1.0499 0.02050 0.01101 -0.0596 0.4044 1.0000
6.500 1.0745 0.02090 0.01157 -0.0591 0.3936 1.0000
6.750 1.0999 0.02134 0.01204 -0.0588 0.3848 1.0000
7.000 1.1248 0.02176 0.01254 -0.0583 0.3753 1.0000
7.250 1.1490 0.02221 0.01315 -0.0579 0.3652 1.0000
7.500 1.1737 0.02262 0.01359 -0.0574 0.3553 1.0000
7.750 1.1973 0.02301 0.01409 -0.0567 0.3437 1.0000
8.000 1.2198 0.02339 0.01462 -0.0560 0.3303 1.0000
8.250 1.2418 0.02377 0.01513 -0.0551 0.3160 1.0000
8.500 1.2633 0.02418 0.01566 -0.0542 0.3010 1.0000
8.750 1.2839 0.02465 0.01621 -0.0532 0.2851 1.0000
9.000 1.3038 0.02518 0.01682 -0.0521 0.2692 1.0000
9.250 1.3228 0.02577 0.01750 -0.0509 0.2536 1.0000
9.500 1.3408 0.02641 0.01819 -0.0496 0.2383 1.0000
9.750 1.3570 0.02707 0.01891 -0.0482 0.2216 1.0000
10.000 1.3721 0.02784 0.01977 -0.0467 0.2050 1.0000
10.250 1.3860 0.02876 0.02076 -0.0451 0.1904 1.0000
10.500 1.3974 0.02984 0.02191 -0.0433 0.1760 1.0000
10.750 1.4049 0.03113 0.02322 -0.0412 0.1613 1.0000
11.000 1.4078 0.03272 0.02478 -0.0386 0.1479 1.0000
11.250 1.4055 0.03456 0.02658 -0.0355 0.1365 1.0000
11.500 1.4022 0.03676 0.02870 -0.0328 0.1259 1.0000
11.750 1.3990 0.03914 0.03111 -0.0304 0.1152 1.0000
12.000 1.3934 0.04178 0.03392 -0.0285 0.1040 1.0000
12.250 1.3854 0.04481 0.03715 -0.0273 0.0924 1.0000
12.500 1.3778 0.04813 0.04068 -0.0270 0.0810 1.0000
12.750 1.3703 0.05179 0.04440 -0.0274 0.0732 1.0000
13.000 1.3606 0.05595 0.04847 -0.0282 0.0685 1.0000
13.250 1.3539 0.05975 0.05230 -0.0280 0.0640 1.0000
13.500 1.3498 0.06309 0.05555 -0.0273 0.0604 1.0000
13.750 1.3552 0.06533 0.05775 -0.0250 0.0568 1.0000
14.000 1.3572 0.06835 0.06092 -0.0240 0.0541 1.0000
14.250 1.3619 0.07105 0.06363 -0.0229 0.0514 1.0000
14.500 1.3742 0.07359 0.06614 -0.0205 0.0485 1.0000
14.750 1.3652 0.07800 0.07085 -0.0213 0.0476 1.0000
15.000 1.3560 0.08267 0.07580 -0.0223 0.0469 1.0000
15.250 1.3454 0.08766 0.08105 -0.0236 0.0464 1.0000
15.500 1.3322 0.09316 0.08681 -0.0254 0.0460 1.0000
15.750 1.3166 0.09925 0.09316 -0.0278 0.0459 1.0000
16.000 1.2981 0.10607 0.10023 -0.0311 0.0459 1.0000
16.250 1.2768 0.11379 0.10819 -0.0353 0.0460 1.0000
16.500 1.2526 0.12254 0.11718 -0.0405 0.0464 1.0000
16.750 1.2256 0.13249 0.12734 -0.0468 0.0470 1.0000
17.000 1.1959 0.14385 0.13887 -0.0542 0.0477 1.0000
17.250 1.1661 0.15624 0.15138 -0.0622 0.0486 1.0000
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Polar data table (+)
Polar graphs
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