GOE 418 AIRFOIL (goe418-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 418 AIRFOIL (goe418-il) Reynolds number: 200,000 Max Cl/Cd: 71.64 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe418-il-200000-n5.txt Download as CSV file: xf-goe418-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 418 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2875 0.10055 0.09647 -0.0412 1.0000 0.0484
-10.000 -0.2967 0.09631 0.09226 -0.0423 1.0000 0.0488
-9.750 -0.3074 0.09230 0.08830 -0.0430 1.0000 0.0494
-9.500 -0.2900 0.09015 0.08618 -0.0450 0.9960 0.0498
-9.250 -0.2725 0.08751 0.08355 -0.0477 0.9852 0.0505
-9.000 -0.2590 0.08389 0.07993 -0.0516 0.9744 0.0513
-8.500 -0.3876 0.02922 0.02366 -0.1071 0.9151 0.0602
-8.250 -0.3541 0.02933 0.02383 -0.1078 0.9062 0.0608
-8.000 -0.3237 0.02914 0.02363 -0.1084 0.8961 0.0614
-7.750 -0.2963 0.02810 0.02245 -0.1091 0.8851 0.0624
-7.500 -0.2796 0.02531 0.01923 -0.1092 0.8720 0.0642
-7.250 -0.2622 0.02233 0.01561 -0.1090 0.8599 0.0663
-7.000 -0.2351 0.02212 0.01539 -0.1087 0.8473 0.0670
-6.750 -0.2091 0.02187 0.01511 -0.1082 0.8336 0.0680
-6.500 -0.1834 0.02142 0.01454 -0.1077 0.8198 0.0692
-6.250 -0.1592 0.02049 0.01334 -0.1071 0.8055 0.0710
-6.000 -0.1361 0.01930 0.01180 -0.1064 0.7905 0.0729
-5.750 -0.1100 0.01910 0.01158 -0.1058 0.7759 0.0738
-5.500 -0.0838 0.01892 0.01132 -0.1052 0.7612 0.0750
-5.250 -0.0580 0.01860 0.01085 -0.1046 0.7464 0.0767
-5.000 -0.0328 0.01799 0.00998 -0.1039 0.7316 0.0790
-4.750 -0.0072 0.01755 0.00938 -0.1032 0.7186 0.0806
-4.500 0.0192 0.01741 0.00918 -0.1027 0.7070 0.0819
-4.250 0.0454 0.01723 0.00892 -0.1021 0.6954 0.0837
-4.000 0.0716 0.01693 0.00843 -0.1015 0.6852 0.0863
-3.750 0.0978 0.01658 0.00790 -0.1009 0.6753 0.0886
-3.500 0.1244 0.01643 0.00772 -0.1004 0.6670 0.0901
-3.250 0.1510 0.01628 0.00753 -0.0999 0.6584 0.0922
-3.000 0.1777 0.01611 0.00721 -0.0994 0.6504 0.0950
-2.750 0.2042 0.01589 0.00684 -0.0989 0.6416 0.0977
-2.500 0.2304 0.01571 0.00665 -0.0983 0.6320 0.0996
-2.250 0.2569 0.01559 0.00650 -0.0977 0.6234 0.1020
-2.000 0.2835 0.01546 0.00630 -0.0972 0.6155 0.1048
-1.750 0.3104 0.01537 0.00607 -0.0967 0.6093 0.1076
-1.500 0.3370 0.01513 0.00586 -0.0963 0.6028 0.1100
-1.250 0.3637 0.01500 0.00575 -0.0958 0.5963 0.1125
-1.000 0.3905 0.01492 0.00563 -0.0953 0.5906 0.1154
-0.750 0.4173 0.01484 0.00551 -0.0948 0.5848 0.1184
-0.500 0.4440 0.01476 0.00540 -0.0943 0.5777 0.1209
-0.250 0.4700 0.01457 0.00524 -0.0937 0.5708 0.1238
0.000 0.4964 0.01449 0.00518 -0.0932 0.5642 0.1268
0.250 0.5227 0.01441 0.00511 -0.0926 0.5564 0.1299
0.500 0.5488 0.01438 0.00502 -0.0920 0.5492 0.1327
0.750 0.5750 0.01432 0.00498 -0.0914 0.5416 0.1354
1.000 0.6006 0.01420 0.00491 -0.0907 0.5336 0.1388
1.250 0.6263 0.01417 0.00488 -0.0901 0.5258 0.1421
1.500 0.6520 0.01413 0.00487 -0.0894 0.5169 0.1458
1.750 0.6776 0.01415 0.00484 -0.0887 0.5093 0.1500
2.000 0.7033 0.01410 0.00488 -0.0881 0.5012 0.1551
2.250 0.7285 0.01410 0.00490 -0.0873 0.4929 0.1614
2.500 0.7540 0.01411 0.00495 -0.0867 0.4846 0.1696
2.750 0.7789 0.01412 0.00501 -0.0859 0.4755 0.1847
3.000 0.8034 0.01409 0.00513 -0.0851 0.4659 0.2196
3.250 0.8272 0.01406 0.00524 -0.0842 0.4558 0.2813
4.250 0.9464 0.01336 0.00587 -0.0854 0.4068 1.0000
4.500 0.9688 0.01360 0.00602 -0.0842 0.3941 1.0000
4.750 0.9907 0.01388 0.00620 -0.0830 0.3824 1.0000
5.000 1.0130 0.01414 0.00641 -0.0818 0.3700 1.0000
5.250 1.0344 0.01445 0.00663 -0.0805 0.3575 1.0000
5.500 1.0549 0.01479 0.00688 -0.0791 0.3453 1.0000
5.750 1.0758 0.01512 0.00716 -0.0778 0.3331 1.0000
6.000 1.0968 0.01545 0.00744 -0.0765 0.3231 1.0000
6.250 1.1166 0.01583 0.00776 -0.0750 0.3128 1.0000
6.500 1.1371 0.01616 0.00808 -0.0736 0.3020 1.0000
6.750 1.1559 0.01656 0.00843 -0.0720 0.2910 1.0000
7.000 1.1741 0.01697 0.00880 -0.0704 0.2783 1.0000
7.250 1.1917 0.01740 0.00920 -0.0686 0.2640 1.0000
7.500 1.2069 0.01789 0.00963 -0.0665 0.2472 1.0000
7.750 1.2182 0.01847 0.01011 -0.0638 0.2280 1.0000
8.000 1.2272 0.01915 0.01068 -0.0608 0.2065 1.0000
8.250 1.2347 0.01995 0.01135 -0.0577 0.1871 1.0000
8.500 1.2430 0.02078 0.01210 -0.0550 0.1742 1.0000
8.750 1.2521 0.02161 0.01288 -0.0524 0.1659 1.0000
9.000 1.2626 0.02240 0.01366 -0.0502 0.1604 1.0000
9.250 1.2712 0.02332 0.01457 -0.0479 0.1556 1.0000
9.500 1.2809 0.02424 0.01550 -0.0459 0.1522 1.0000
9.750 1.2912 0.02516 0.01645 -0.0440 0.1490 1.0000
10.000 1.3003 0.02620 0.01751 -0.0421 0.1461 1.0000
10.250 1.3079 0.02738 0.01869 -0.0403 0.1432 1.0000
10.500 1.3139 0.02872 0.02003 -0.0385 0.1408 1.0000
10.750 1.3244 0.02982 0.02119 -0.0371 0.1388 1.0000
11.000 1.3343 0.03100 0.02243 -0.0358 0.1367 1.0000
11.250 1.3432 0.03229 0.02378 -0.0345 0.1345 1.0000
11.500 1.3508 0.03372 0.02525 -0.0333 0.1324 1.0000
11.750 1.3580 0.03524 0.02679 -0.0322 0.1306 1.0000
12.000 1.3643 0.03687 0.02843 -0.0311 0.1289 1.0000
12.250 1.3713 0.03848 0.03005 -0.0301 0.1273 1.0000
12.500 1.3813 0.03988 0.03155 -0.0293 0.1257 1.0000
12.750 1.3901 0.04140 0.03317 -0.0286 0.1238 1.0000
13.000 1.3981 0.04304 0.03489 -0.0280 0.1217 1.0000
13.250 1.4047 0.04483 0.03672 -0.0274 0.1196 1.0000
13.500 1.4107 0.04669 0.03862 -0.0268 0.1177 1.0000
13.750 1.4162 0.04861 0.04055 -0.0262 0.1159 1.0000
14.000 1.4234 0.05042 0.04241 -0.0257 0.1143 1.0000
14.250 1.4310 0.05226 0.04437 -0.0254 0.1127 1.0000
14.500 1.4378 0.05420 0.04643 -0.0251 0.1110 1.0000
14.750 1.4436 0.05628 0.04860 -0.0250 0.1091 1.0000
15.000 1.4484 0.05851 0.05091 -0.0249 0.1071 1.0000
15.250 1.4522 0.06085 0.05330 -0.0248 0.1053 1.0000
15.500 1.4561 0.06318 0.05563 -0.0247 0.1034 1.0000
15.750 1.4602 0.06564 0.05824 -0.0250 0.1015 1.0000
16.000 1.4640 0.06819 0.06094 -0.0252 0.0993 1.0000
16.250 1.4663 0.07097 0.06385 -0.0256 0.0969 1.0000
16.500 1.4671 0.07396 0.06692 -0.0262 0.0947 1.0000
16.750 1.4672 0.07706 0.07005 -0.0268 0.0927 1.0000
17.000 1.4693 0.08007 0.07327 -0.0275 0.0896 1.0000
17.250 1.4692 0.08340 0.07673 -0.0284 0.0863 1.0000
17.500 1.4666 0.08715 0.08056 -0.0295 0.0834 1.0000
17.750 1.4665 0.09061 0.08418 -0.0305 0.0791 1.0000
18.000 1.4622 0.09474 0.08840 -0.0320 0.0754 1.0000
18.250 1.4586 0.09879 0.09255 -0.0334 0.0710 1.0000
18.500 1.4514 0.10350 0.09731 -0.0353 0.0675 1.0000
18.750 1.4440 0.10829 0.10217 -0.0372 0.0640 1.0000
19.000 1.4345 0.11348 0.10740 -0.0394 0.0615 1.0000
19.250 1.4265 0.11844 0.11244 -0.0416 0.0590 1.0000
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