GOE 430 AIRFOIL (goe430-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 430 AIRFOIL (goe430-il) Reynolds number: 100,000 Max Cl/Cd: 60.87 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe430-il-100000-n5.txt Download as CSV file: xf-goe430-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 430 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3390 0.11889 0.11328 -0.0493 1.0000 0.0673
-11.250 -0.3500 0.11449 0.10893 -0.0507 1.0000 0.0681
-11.000 -0.3641 0.10981 0.10430 -0.0520 1.0000 0.0686
-10.750 -0.3632 0.10794 0.10248 -0.0506 1.0000 0.0691
-10.500 -0.3718 0.10489 0.09948 -0.0500 1.0000 0.0692
-10.250 -0.3814 0.10204 0.09668 -0.0490 1.0000 0.0692
-10.000 -0.3899 0.09968 0.09437 -0.0476 1.0000 0.0695
-9.750 -0.3939 0.09826 0.09299 -0.0457 1.0000 0.0700
-9.500 -0.3887 0.09611 0.09085 -0.0461 0.9982 0.0710
-9.250 -0.3753 0.09227 0.08698 -0.0502 0.9940 0.0722
-9.000 -0.3705 0.08701 0.08171 -0.0551 0.9883 0.0728
-8.500 -0.4487 0.04018 0.03378 -0.1146 0.9579 0.0744
-8.250 -0.4263 0.03657 0.02972 -0.1191 0.9509 0.0761
-8.000 -0.3942 0.03342 0.02606 -0.1239 0.9468 0.0778
-7.750 -0.3583 0.03096 0.02312 -0.1281 0.9440 0.0791
-7.500 -0.3304 0.02945 0.02141 -0.1295 0.9387 0.0803
-7.250 -0.2999 0.02841 0.02030 -0.1310 0.9339 0.0816
-7.000 -0.2647 0.02744 0.01925 -0.1332 0.9306 0.0835
-6.750 -0.2269 0.02649 0.01814 -0.1359 0.9281 0.0862
-6.500 -0.1990 0.02563 0.01711 -0.1366 0.9222 0.0888
-6.250 -0.1665 0.02471 0.01599 -0.1380 0.9174 0.0914
-6.000 -0.1311 0.02399 0.01527 -0.1399 0.9139 0.0940
-5.750 -0.0937 0.02332 0.01454 -0.1421 0.9112 0.0975
-5.500 -0.0681 0.02281 0.01394 -0.1420 0.9036 0.1014
-5.250 -0.0335 0.02223 0.01333 -0.1435 0.8987 0.1069
-5.000 0.0050 0.02165 0.01266 -0.1456 0.8949 0.1156
-4.750 0.0319 0.02126 0.01229 -0.1455 0.8858 0.1234
-4.500 0.0683 0.02067 0.01160 -0.1470 0.8800 0.1351
-4.250 0.0980 0.02027 0.01109 -0.1473 0.8712 0.1471
-4.000 0.1311 0.01980 0.01062 -0.1482 0.8643 0.1593
-3.750 0.1612 0.01944 0.01025 -0.1486 0.8570 0.1709
-3.500 0.1909 0.01914 0.00992 -0.1489 0.8495 0.1820
-3.250 0.2248 0.01877 0.00953 -0.1499 0.8448 0.1934
-3.000 0.2500 0.01863 0.00945 -0.1494 0.8348 0.2052
-2.750 0.2827 0.01835 0.00918 -0.1501 0.8292 0.2214
-2.500 0.3089 0.01827 0.00913 -0.1498 0.8195 0.2369
-2.250 0.3407 0.01800 0.00888 -0.1503 0.8133 0.2530
-2.000 0.3674 0.01786 0.00877 -0.1500 0.8034 0.2666
-1.750 0.3992 0.01757 0.00847 -0.1504 0.7966 0.2835
-1.500 0.4256 0.01745 0.00838 -0.1501 0.7860 0.3021
-1.250 0.4561 0.01721 0.00815 -0.1503 0.7781 0.3233
-1.000 0.4839 0.01708 0.00807 -0.1501 0.7678 0.3437
-0.750 0.5127 0.01693 0.00798 -0.1501 0.7585 0.3650
-0.500 0.5422 0.01680 0.00789 -0.1501 0.7495 0.3889
-0.250 0.5699 0.01676 0.00791 -0.1499 0.7390 0.4139
0.000 0.5998 0.01666 0.00783 -0.1499 0.7302 0.4406
0.250 0.6274 0.01665 0.00786 -0.1496 0.7193 0.4654
0.500 0.6556 0.01664 0.00786 -0.1494 0.7088 0.4899
1.000 0.7120 0.01661 0.00787 -0.1488 0.6866 0.5438
1.250 0.7389 0.01664 0.00793 -0.1483 0.6742 0.5717
1.500 0.7664 0.01668 0.00798 -0.1478 0.6625 0.6003
1.750 0.7939 0.01674 0.00802 -0.1473 0.6512 0.6291
2.000 0.8200 0.01684 0.00815 -0.1467 0.6395 0.6558
2.250 0.8468 0.01693 0.00824 -0.1462 0.6289 0.6831
2.500 0.8733 0.01699 0.00830 -0.1457 0.6183 0.7087
2.750 0.8983 0.01707 0.00844 -0.1449 0.6071 0.7339
3.000 0.9234 0.01711 0.00852 -0.1441 0.5976 0.7637
3.250 0.9453 0.01708 0.00865 -0.1425 0.5877 0.8100
3.500 0.9678 0.01701 0.00870 -0.1411 0.5787 1.0000
3.750 0.9958 0.01729 0.00890 -0.1412 0.5694 1.0000
4.000 1.0229 0.01758 0.00916 -0.1411 0.5599 1.0000
4.250 1.0504 0.01786 0.00938 -0.1410 0.5515 1.0000
4.500 1.0762 0.01817 0.00969 -0.1407 0.5412 1.0000
4.750 1.1020 0.01846 0.00992 -0.1402 0.5304 1.0000
5.000 1.1271 0.01875 0.01019 -0.1397 0.5193 1.0000
5.250 1.1518 0.01908 0.01053 -0.1391 0.5087 1.0000
5.500 1.1764 0.01940 0.01082 -0.1385 0.4981 1.0000
5.750 1.2003 0.01973 0.01114 -0.1377 0.4866 1.0000
6.000 1.2233 0.02010 0.01152 -0.1368 0.4744 1.0000
6.250 1.2461 0.02047 0.01190 -0.1359 0.4626 1.0000
6.500 1.2684 0.02087 0.01227 -0.1349 0.4504 1.0000
6.750 1.2896 0.02130 0.01271 -0.1337 0.4372 1.0000
7.000 1.3097 0.02176 0.01320 -0.1324 0.4227 1.0000
7.250 1.3289 0.02226 0.01371 -0.1310 0.4077 1.0000
7.500 1.3467 0.02279 0.01427 -0.1293 0.3907 1.0000
7.750 1.3627 0.02337 0.01487 -0.1274 0.3711 1.0000
8.000 1.3776 0.02398 0.01553 -0.1254 0.3474 1.0000
8.250 1.3899 0.02469 0.01620 -0.1230 0.3203 1.0000
8.500 1.3972 0.02557 0.01696 -0.1199 0.2927 1.0000
8.750 1.4035 0.02666 0.01790 -0.1169 0.2724 1.0000
9.000 1.4101 0.02786 0.01901 -0.1141 0.2580 1.0000
9.250 1.4166 0.02914 0.02022 -0.1115 0.2470 1.0000
9.500 1.4257 0.03035 0.02144 -0.1093 0.2375 1.0000
9.750 1.4330 0.03170 0.02278 -0.1069 0.2297 1.0000
10.000 1.4427 0.03295 0.02410 -0.1050 0.2217 1.0000
10.500 1.4585 0.03578 0.02703 -0.1010 0.2061 1.0000
10.750 1.4635 0.03743 0.02865 -0.0988 0.1982 1.0000
11.000 1.4714 0.03891 0.03028 -0.0972 0.1885 1.0000
11.250 1.4754 0.04070 0.03208 -0.0953 0.1799 1.0000
11.500 1.4813 0.04241 0.03393 -0.0938 0.1700 1.0000
11.750 1.4860 0.04426 0.03586 -0.0923 0.1612 1.0000
12.000 1.4894 0.04629 0.03797 -0.0909 0.1526 1.0000
12.250 1.4945 0.04823 0.04004 -0.0897 0.1445 1.0000
12.500 1.4959 0.05056 0.04241 -0.0885 0.1374 1.0000
12.750 1.4999 0.05274 0.04470 -0.0875 0.1295 1.0000
13.000 1.5000 0.05535 0.04735 -0.0865 0.1227 1.0000
13.250 1.5017 0.05788 0.04999 -0.0857 0.1156 1.0000
13.500 1.5007 0.06080 0.05296 -0.0850 0.1095 1.0000
13.750 1.4996 0.06384 0.05609 -0.0845 0.1023 1.0000
14.000 1.4965 0.06720 0.05949 -0.0841 0.0961 1.0000
14.250 1.4918 0.07085 0.06320 -0.0839 0.0893 1.0000
14.500 1.4870 0.07464 0.06706 -0.0839 0.0825 1.0000
14.750 1.4803 0.07878 0.07126 -0.0841 0.0761 1.0000
15.000 1.4774 0.08251 0.07516 -0.0843 0.0685 1.0000
15.250 1.4730 0.08655 0.07934 -0.0847 0.0592 1.0000
15.500 1.4656 0.09111 0.08398 -0.0854 0.0489 1.0000
15.750 1.4541 0.09642 0.08931 -0.0866 0.0434 1.0000
16.000 1.4414 0.10203 0.09494 -0.0881 0.0401 1.0000
16.250 1.4290 0.10774 0.10074 -0.0898 0.0379 1.0000
16.500 1.4162 0.11367 0.10676 -0.0918 0.0361 1.0000
16.750 1.4029 0.11985 0.11305 -0.0941 0.0348 1.0000
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