GOE 602 AIRFOIL (goe602-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 602 AIRFOIL (goe602-il) Reynolds number: 100,000 Max Cl/Cd: 57.57 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe602-il-100000.txt Download as CSV file: xf-goe602-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 602 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3678 0.10260 0.09772 -0.0350 1.0000 0.0946
-8.750 -0.3854 0.10101 0.09625 -0.0369 1.0000 0.0977
-8.500 -0.4067 0.09968 0.09506 -0.0378 1.0000 0.0983
-8.250 -0.3835 0.09450 0.08984 -0.0342 1.0000 0.1028
-8.000 -0.3849 0.09224 0.08764 -0.0326 1.0000 0.1065
-7.750 -0.3986 0.09043 0.08593 -0.0313 1.0000 0.1094
-7.500 -0.4213 0.08908 0.08471 -0.0295 1.0000 0.1109
-7.250 -0.4465 0.08688 0.08263 -0.0323 1.0000 0.1123
-7.000 -0.4708 0.08403 0.07971 -0.0381 1.0000 0.1132
-6.750 -0.4482 0.08060 0.07643 -0.0275 1.0000 0.1172
-6.500 -0.4499 0.07814 0.07400 -0.0262 1.0000 0.1210
-6.250 -0.4711 0.07418 0.06982 -0.0369 1.0000 0.1280
-6.000 -0.4618 0.07070 0.06654 -0.0307 1.0000 0.1302
-5.750 -0.4568 0.06846 0.06434 -0.0278 1.0000 0.1345
-5.500 -0.4559 0.06403 0.05973 -0.0324 1.0000 0.1443
-5.250 -0.4476 0.06176 0.05726 -0.0339 1.0000 0.1568
-5.000 -0.4411 0.05817 0.05381 -0.0313 1.0000 0.1603
-4.750 -0.4318 0.05548 0.05104 -0.0313 1.0000 0.1746
-4.500 -0.4217 0.05315 0.04869 -0.0304 1.0000 0.1897
-4.250 -0.4102 0.05086 0.04637 -0.0294 1.0000 0.2053
-4.000 -0.3443 0.03395 0.02694 -0.0414 1.0000 0.0870
-3.750 -0.3205 0.03217 0.02446 -0.0405 1.0000 0.0845
-3.500 -0.2985 0.02969 0.02158 -0.0401 1.0000 0.0855
-3.250 -0.2608 0.02764 0.01903 -0.0420 0.9958 0.0853
-3.000 -0.2206 0.02596 0.01724 -0.0450 0.9894 0.0906
-2.750 -0.1765 0.02490 0.01586 -0.0480 0.9833 0.0949
-2.500 -0.1372 0.02392 0.01460 -0.0500 0.9752 0.0995
-2.250 -0.0967 0.02313 0.01386 -0.0527 0.9680 0.1096
-2.000 -0.0576 0.02230 0.01311 -0.0549 0.9600 0.1194
-1.750 -0.0211 0.02162 0.01248 -0.0566 0.9514 0.1417
-1.500 0.0122 0.01917 0.01217 -0.0580 0.9455 0.5468
-1.250 0.0735 0.01825 0.01212 -0.0632 0.9413 1.0000
-1.000 0.1139 0.01843 0.01197 -0.0658 0.9314 1.0000
-0.750 0.1507 0.01858 0.01187 -0.0678 0.9206 1.0000
-0.500 0.1941 0.01870 0.01178 -0.0709 0.9121 1.0000
-0.250 0.2347 0.01875 0.01164 -0.0734 0.9026 1.0000
0.000 0.2697 0.01881 0.01157 -0.0748 0.8914 1.0000
0.250 0.3211 0.01867 0.01129 -0.0791 0.8857 1.0000
0.500 0.3550 0.01863 0.01116 -0.0801 0.8739 1.0000
0.750 0.3905 0.01856 0.01101 -0.0814 0.8628 1.0000
1.000 0.4440 0.01814 0.01054 -0.0858 0.8576 1.0000
1.250 0.4765 0.01802 0.01037 -0.0863 0.8453 1.0000
1.500 0.5108 0.01783 0.01016 -0.0870 0.8337 1.0000
1.750 0.5481 0.01755 0.00987 -0.0882 0.8231 1.0000
2.000 0.5917 0.01706 0.00937 -0.0903 0.8145 1.0000
2.250 0.6235 0.01684 0.00914 -0.0904 0.8011 1.0000
2.500 0.6557 0.01661 0.00893 -0.0906 0.7874 1.0000
2.750 0.6879 0.01639 0.00870 -0.0907 0.7732 1.0000
3.000 0.7196 0.01621 0.00851 -0.0907 0.7583 1.0000
3.250 0.7508 0.01608 0.00838 -0.0906 0.7429 1.0000
3.500 0.7784 0.01609 0.00839 -0.0900 0.7259 1.0000
3.750 0.8044 0.01618 0.00848 -0.0892 0.7078 1.0000
4.000 0.8315 0.01625 0.00854 -0.0885 0.6895 1.0000
4.250 0.8595 0.01632 0.00859 -0.0880 0.6712 1.0000
4.500 0.8834 0.01650 0.00877 -0.0868 0.6510 1.0000
4.750 0.9077 0.01669 0.00896 -0.0857 0.6310 1.0000
5.000 0.9338 0.01689 0.00912 -0.0849 0.6121 1.0000
5.250 0.9558 0.01719 0.00950 -0.0835 0.5923 1.0000
5.500 0.9789 0.01746 0.00979 -0.0823 0.5722 1.0000
5.750 1.0012 0.01771 0.01003 -0.0808 0.5505 1.0000
6.000 1.0203 0.01786 0.01013 -0.0787 0.5228 1.0000
6.250 1.0361 0.01802 0.01029 -0.0760 0.4911 1.0000
6.500 1.0530 0.01829 0.01054 -0.0737 0.4622 1.0000
6.750 1.0695 0.01862 0.01087 -0.0714 0.4334 1.0000
7.000 1.0842 0.01898 0.01123 -0.0689 0.4010 1.0000
7.250 1.0973 0.01943 0.01162 -0.0661 0.3652 1.0000
7.500 1.1074 0.02001 0.01212 -0.0629 0.3163 1.0000
7.750 1.1133 0.02100 0.01277 -0.0592 0.2501 1.0000
8.000 1.1125 0.02276 0.01390 -0.0550 0.1519 1.0000
8.250 1.1069 0.02513 0.01562 -0.0503 0.0891 1.0000
8.500 1.1089 0.02679 0.01719 -0.0464 0.0704 1.0000
8.750 1.1134 0.02824 0.01862 -0.0430 0.0617 1.0000
9.000 1.1197 0.02957 0.02007 -0.0400 0.0568 1.0000
9.250 1.1236 0.03110 0.02164 -0.0369 0.0538 1.0000
9.500 1.1259 0.03288 0.02348 -0.0338 0.0518 1.0000
9.750 1.1338 0.03454 0.02526 -0.0314 0.0503 1.0000
10.000 1.1452 0.03624 0.02704 -0.0294 0.0481 1.0000
10.250 1.1580 0.03798 0.02880 -0.0278 0.0454 1.0000
10.500 1.1833 0.04034 0.03109 -0.0274 0.0434 1.0000
10.750 1.2363 0.04441 0.03528 -0.0303 0.0426 1.0000
11.000 1.2703 0.04850 0.03972 -0.0315 0.0426 1.0000
11.250 1.2864 0.05190 0.04350 -0.0303 0.0428 1.0000
11.500 1.2925 0.05546 0.04741 -0.0282 0.0428 1.0000
11.750 1.2914 0.05881 0.05109 -0.0254 0.0428 1.0000
12.000 1.2849 0.06227 0.05486 -0.0224 0.0427 1.0000
12.250 1.2755 0.06493 0.05781 -0.0193 0.0429 1.0000
12.500 1.2628 0.06783 0.06099 -0.0165 0.0431 1.0000
12.750 1.2463 0.07081 0.06427 -0.0141 0.0435 1.0000
13.000 1.2239 0.07453 0.06834 -0.0125 0.0440 1.0000
13.250 1.1856 0.07982 0.07405 -0.0122 0.0451 1.0000
13.500 1.1464 0.08680 0.08139 -0.0141 0.0464 1.0000
13.750 1.1137 0.09422 0.08906 -0.0174 0.0474 1.0000
14.000 1.0817 0.10267 0.09771 -0.0221 0.0486 1.0000
14.250 1.0526 0.11176 0.10694 -0.0276 0.0497 1.0000
14.500 1.0280 0.12114 0.11637 -0.0334 0.0508 1.0000
14.750 1.0120 0.12964 0.12490 -0.0381 0.0517 1.0000
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Polar data table (+)
Polar graphs
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