GOE 410 AIRFOIL (goe410-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 410 AIRFOIL (goe410-il) Reynolds number: 200,000 Max Cl/Cd: 45.16 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe410-il-200000-n5.txt Download as CSV file: xf-goe410-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 410 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
------ -------- --------- --------- -------- -------- --------
-19.000 -1.0702 0.12310 0.11818 0.0032 1.0000 0.0536
-18.750 -1.1055 0.11236 0.10721 -0.0032 1.0000 0.0548
-18.500 -1.1302 0.10400 0.09862 -0.0080 1.0000 0.0560
-18.250 -1.1384 0.09883 0.09341 -0.0109 1.0000 0.0570
-18.000 -1.1475 0.09359 0.08809 -0.0137 1.0000 0.0580
-17.750 -1.1574 0.08831 0.08269 -0.0166 1.0000 0.0593
-17.500 -1.1667 0.08323 0.07748 -0.0192 1.0000 0.0607
-17.250 -1.1755 0.07837 0.07244 -0.0216 1.0000 0.0623
-17.000 -1.1800 0.07434 0.06834 -0.0236 1.0000 0.0635
-16.750 -1.1833 0.07059 0.06453 -0.0253 1.0000 0.0648
-16.500 -1.1864 0.06693 0.06078 -0.0270 1.0000 0.0663
-16.250 -1.1889 0.06345 0.05717 -0.0284 1.0000 0.0680
-16.000 -1.1910 0.06009 0.05362 -0.0297 1.0000 0.0698
-15.750 -1.1908 0.05722 0.05072 -0.0306 1.0000 0.0711
-15.500 -1.1902 0.05448 0.04793 -0.0315 1.0000 0.0724
-15.250 -1.1889 0.05183 0.04520 -0.0323 1.0000 0.0740
-15.000 -1.1867 0.04933 0.04259 -0.0330 1.0000 0.0758
-14.750 -1.1836 0.04696 0.04007 -0.0335 1.0000 0.0775
-14.500 -1.1795 0.04477 0.03782 -0.0338 1.0000 0.0790
-14.250 -1.1751 0.04271 0.03573 -0.0340 1.0000 0.0804
-14.000 -1.1697 0.04076 0.03373 -0.0342 1.0000 0.0820
-13.750 -1.1633 0.03896 0.03184 -0.0342 1.0000 0.0838
-13.500 -1.1558 0.03729 0.03007 -0.0341 1.0000 0.0855
-13.250 -1.1473 0.03574 0.02837 -0.0338 1.0000 0.0871
-13.000 -1.1398 0.03420 0.02685 -0.0334 1.0000 0.0886
-12.750 -1.1317 0.03279 0.02541 -0.0329 1.0000 0.0901
-12.500 -1.1225 0.03150 0.02407 -0.0323 1.0000 0.0918
-12.250 -1.1124 0.03033 0.02283 -0.0316 1.0000 0.0936
-12.000 -1.1013 0.02925 0.02166 -0.0307 1.0000 0.0954
-11.750 -1.0894 0.02827 0.02057 -0.0298 1.0000 0.0970
-11.500 -1.0796 0.02723 0.01955 -0.0285 1.0000 0.0986
-11.250 -1.0688 0.02635 0.01866 -0.0272 1.0000 0.1001
-11.000 -1.0572 0.02557 0.01785 -0.0257 1.0000 0.1020
-10.750 -1.0448 0.02489 0.01711 -0.0240 1.0000 0.1041
-10.500 -1.0313 0.02430 0.01644 -0.0223 1.0000 0.1066
-10.250 -1.0181 0.02368 0.01580 -0.0206 1.0000 0.1090
-10.000 -1.0030 0.02308 0.01523 -0.0191 1.0000 0.1116
-9.750 -0.9856 0.02254 0.01467 -0.0178 1.0000 0.1140
-9.500 -0.9670 0.02201 0.01409 -0.0166 1.0000 0.1164
-9.250 -0.9477 0.02148 0.01351 -0.0155 1.0000 0.1185
-9.000 -0.9287 0.02092 0.01293 -0.0144 1.0000 0.1206
-8.750 -0.9102 0.02033 0.01238 -0.0132 1.0000 0.1229
-8.500 -0.8905 0.01982 0.01188 -0.0120 1.0000 0.1254
-8.250 -0.8701 0.01935 0.01139 -0.0110 1.0000 0.1281
-8.000 -0.8492 0.01892 0.01092 -0.0099 1.0000 0.1308
-7.750 -0.8286 0.01848 0.01047 -0.0089 1.0000 0.1335
-7.500 -0.8098 0.01793 0.00999 -0.0076 1.0000 0.1366
-7.250 -0.7890 0.01749 0.00956 -0.0066 0.9988 0.1402
-7.000 -0.7515 0.01705 0.00909 -0.0088 0.9670 0.1452
-6.750 -0.7137 0.01654 0.00857 -0.0111 0.9344 0.1501
-6.500 -0.6798 0.01606 0.00807 -0.0125 0.8990 0.1555
-6.250 -0.6510 0.01574 0.00765 -0.0126 0.8666 0.1609
-6.000 -0.6260 0.01539 0.00724 -0.0120 0.8394 0.1664
-5.750 -0.6026 0.01506 0.00686 -0.0111 0.8153 0.1734
-5.500 -0.5792 0.01475 0.00650 -0.0102 0.7935 0.1818
-5.250 -0.5564 0.01439 0.00615 -0.0093 0.7732 0.1946
-5.000 -0.5341 0.01395 0.00580 -0.0084 0.7536 0.2182
-4.750 -0.5116 0.01353 0.00551 -0.0074 0.7343 0.2574
-4.500 -0.4877 0.01325 0.00529 -0.0067 0.7156 0.2916
-4.250 -0.4629 0.01304 0.00512 -0.0060 0.6974 0.3170
-4.000 -0.4374 0.01290 0.00497 -0.0053 0.6799 0.3385
-3.750 -0.4115 0.01280 0.00484 -0.0048 0.6635 0.3567
-3.500 -0.3852 0.01273 0.00473 -0.0043 0.6484 0.3724
-3.250 -0.3585 0.01267 0.00463 -0.0038 0.6337 0.3867
-3.000 -0.3316 0.01263 0.00456 -0.0034 0.6208 0.4016
-2.750 -0.3047 0.01263 0.00450 -0.0030 0.6092 0.4170
-2.500 -0.2775 0.01259 0.00447 -0.0026 0.5979 0.4295
-2.250 -0.2501 0.01259 0.00440 -0.0023 0.5883 0.4385
-2.000 -0.2224 0.01257 0.00435 -0.0020 0.5784 0.4475
-1.750 -0.1949 0.01258 0.00430 -0.0017 0.5700 0.4569
-1.500 -0.1670 0.01256 0.00429 -0.0015 0.5617 0.4656
-1.250 -0.1390 0.01258 0.00422 -0.0013 0.5540 0.4730
-1.000 -0.1113 0.01255 0.00421 -0.0010 0.5457 0.4798
-0.750 -0.0834 0.01256 0.00418 -0.0008 0.5365 0.4879
-0.500 -0.0557 0.01256 0.00416 -0.0005 0.5278 0.4957
-0.250 -0.0279 0.01254 0.00416 -0.0002 0.5193 0.5041
0.000 0.0000 0.01259 0.00413 0.0000 0.5122 0.5122
0.250 0.0279 0.01254 0.00416 0.0002 0.5040 0.5193
0.500 0.0557 0.01256 0.00416 0.0005 0.4956 0.5278
0.750 0.0835 0.01256 0.00418 0.0008 0.4878 0.5363
1.000 0.1113 0.01255 0.00421 0.0010 0.4798 0.5455
1.250 0.1390 0.01258 0.00422 0.0013 0.4729 0.5539
1.500 0.1670 0.01256 0.00429 0.0015 0.4656 0.5617
1.750 0.1949 0.01258 0.00430 0.0017 0.4569 0.5700
2.000 0.2224 0.01257 0.00436 0.0020 0.4476 0.5785
2.250 0.2501 0.01259 0.00440 0.0023 0.4385 0.5883
2.500 0.2775 0.01259 0.00447 0.0026 0.4295 0.5979
2.750 0.3047 0.01263 0.00450 0.0030 0.4170 0.6091
3.000 0.3316 0.01263 0.00456 0.0034 0.4016 0.6207
3.250 0.3585 0.01267 0.00463 0.0038 0.3867 0.6337
3.500 0.3852 0.01273 0.00473 0.0043 0.3722 0.6484
3.750 0.4115 0.01280 0.00484 0.0048 0.3566 0.6635
4.000 0.4374 0.01290 0.00497 0.0053 0.3384 0.6799
4.250 0.4629 0.01304 0.00512 0.0060 0.3170 0.6974
4.500 0.4877 0.01325 0.00529 0.0067 0.2915 0.7155
4.750 0.5116 0.01353 0.00551 0.0074 0.2573 0.7343
5.000 0.5341 0.01395 0.00580 0.0084 0.2182 0.7535
5.250 0.5564 0.01439 0.00615 0.0093 0.1945 0.7732
5.500 0.5793 0.01475 0.00650 0.0102 0.1819 0.7935
5.750 0.6026 0.01506 0.00686 0.0111 0.1734 0.8153
6.000 0.6260 0.01540 0.00724 0.0120 0.1664 0.8394
6.250 0.6510 0.01574 0.00765 0.0126 0.1609 0.8666
6.500 0.6798 0.01606 0.00807 0.0125 0.1555 0.8989
6.750 0.7137 0.01654 0.00857 0.0111 0.1501 0.9342
7.000 0.7515 0.01705 0.00908 0.0088 0.1452 0.9669
7.250 0.7891 0.01749 0.00956 0.0065 0.1402 0.9989
7.500 0.8098 0.01793 0.00998 0.0076 0.1366 1.0000
7.750 0.8286 0.01847 0.01047 0.0088 0.1335 1.0000
8.000 0.8493 0.01892 0.01092 0.0099 0.1309 1.0000
8.250 0.8702 0.01935 0.01139 0.0110 0.1281 1.0000
8.500 0.8906 0.01982 0.01188 0.0120 0.1254 1.0000
8.750 0.9102 0.02033 0.01238 0.0131 0.1229 1.0000
9.000 0.9288 0.02091 0.01292 0.0143 0.1206 1.0000
9.250 0.9478 0.02148 0.01351 0.0155 0.1185 1.0000
9.500 0.9671 0.02201 0.01409 0.0166 0.1164 1.0000
9.750 0.9857 0.02254 0.01467 0.0178 0.1141 1.0000
10.000 1.0032 0.02307 0.01522 0.0191 0.1115 1.0000
10.250 1.0184 0.02367 0.01580 0.0205 0.1090 1.0000
10.500 1.0317 0.02430 0.01644 0.0223 0.1067 1.0000
10.750 1.0451 0.02490 0.01711 0.0240 0.1042 1.0000
11.000 1.0576 0.02557 0.01784 0.0256 0.1020 1.0000
11.250 1.0694 0.02634 0.01865 0.0271 0.1002 1.0000
11.500 1.0801 0.02723 0.01954 0.0285 0.0986 1.0000
11.750 1.0899 0.02827 0.02056 0.0297 0.0970 1.0000
12.000 1.1019 0.02924 0.02165 0.0307 0.0954 1.0000
12.250 1.1130 0.03032 0.02282 0.0315 0.0936 1.0000
12.500 1.1232 0.03149 0.02406 0.0322 0.0917 1.0000
12.750 1.1324 0.03277 0.02539 0.0328 0.0901 1.0000
13.000 1.1405 0.03419 0.02683 0.0333 0.0885 1.0000
13.250 1.1482 0.03572 0.02835 0.0337 0.0871 1.0000
13.500 1.1568 0.03726 0.03004 0.0340 0.0854 1.0000
13.750 1.1644 0.03892 0.03180 0.0341 0.0837 1.0000
14.000 1.1709 0.04072 0.03368 0.0341 0.0820 1.0000
14.250 1.1764 0.04266 0.03568 0.0339 0.0804 1.0000
14.500 1.1807 0.04474 0.03778 0.0336 0.0790 1.0000
14.750 1.1846 0.04694 0.04005 0.0333 0.0774 1.0000
15.000 1.1880 0.04929 0.04255 0.0328 0.0757 1.0000
15.250 1.1902 0.05180 0.04517 0.0321 0.0739 1.0000
15.500 1.1917 0.05442 0.04787 0.0314 0.0723 1.0000
15.750 1.1922 0.05717 0.05066 0.0305 0.0710 1.0000
16.000 1.1925 0.06004 0.05357 0.0295 0.0697 1.0000
16.250 1.1906 0.06337 0.05709 0.0282 0.0679 1.0000
16.500 1.1881 0.06685 0.06069 0.0268 0.0663 1.0000
16.750 1.1850 0.07051 0.06445 0.0251 0.0647 1.0000
17.000 1.1820 0.07423 0.06823 0.0234 0.0635 1.0000
17.250 1.1776 0.07823 0.07229 0.0215 0.0623 1.0000
17.500 1.1687 0.08312 0.07737 0.0191 0.0606 1.0000
17.750 1.1594 0.08820 0.08259 0.0164 0.0592 1.0000
18.000 1.1498 0.09342 0.08791 0.0136 0.0580 1.0000
18.250 1.1408 0.09865 0.09322 0.0108 0.0570 1.0000
18.500 1.1326 0.10382 0.09844 0.0079 0.0560 1.0000
18.750 1.1075 0.11226 0.10711 0.0031 0.0548 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 410 AIRFOIL (goe410-il)