GOE 422 AIRFOIL (goe422-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 422 AIRFOIL (goe422-il) Reynolds number: 200,000 Max Cl/Cd: 71.01 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe422-il-200000.txt Download as CSV file: xf-goe422-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 422 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.0499 0.10208 0.09816 -0.1140 0.9437 0.0694
-10.000 0.0616 0.09895 0.09502 -0.1166 0.9388 0.0715
-9.750 0.0392 0.09469 0.09077 -0.1234 0.9270 0.0740
-9.500 0.0606 0.09218 0.08826 -0.1216 0.9220 0.0746
-9.250 0.0747 0.08998 0.08606 -0.1207 0.9145 0.0754
-9.000 0.0871 0.08742 0.08347 -0.1212 0.9097 0.0767
-8.750 0.0919 0.08510 0.08116 -0.1216 0.9004 0.0783
-8.500 0.0455 0.07925 0.07533 -0.1336 0.8855 0.0820
-8.250 0.0722 0.07705 0.07312 -0.1296 0.8824 0.0825
-8.000 0.0911 0.07496 0.07100 -0.1279 0.8785 0.0832
-7.750 0.1028 0.07299 0.06903 -0.1273 0.8717 0.0842
-7.500 0.1111 0.07066 0.06669 -0.1277 0.8648 0.0857
-7.250 0.0691 0.06143 0.05721 -0.1457 0.8515 0.0915
-7.000 0.0905 0.05955 0.05540 -0.1436 0.8470 0.0920
-6.750 0.1103 0.05784 0.05368 -0.1424 0.8431 0.0928
-6.500 0.1226 0.05636 0.05221 -0.1415 0.8357 0.0940
-6.250 0.1169 0.04966 0.04494 -0.1503 0.8277 0.1022
-6.000 0.1408 0.04750 0.04287 -0.1499 0.8238 0.1031
-5.750 0.1545 0.04616 0.04158 -0.1486 0.8160 0.1043
-5.500 0.1378 0.02910 0.02244 -0.1508 0.8095 0.0661
-5.250 0.1651 0.02700 0.02001 -0.1512 0.8056 0.0659
-5.000 0.1815 0.02571 0.01847 -0.1495 0.7977 0.0660
-4.750 0.2062 0.02432 0.01682 -0.1491 0.7921 0.0670
-4.500 0.2367 0.02352 0.01598 -0.1497 0.7877 0.0685
-4.250 0.2595 0.02284 0.01520 -0.1488 0.7812 0.0696
-4.000 0.2838 0.02199 0.01418 -0.1481 0.7745 0.0707
-3.750 0.3139 0.02108 0.01303 -0.1482 0.7696 0.0723
-3.500 0.3412 0.02039 0.01212 -0.1479 0.7639 0.0741
-3.250 0.3642 0.01987 0.01167 -0.1469 0.7556 0.0762
-3.000 0.3954 0.01934 0.01103 -0.1472 0.7496 0.0800
-2.750 0.4199 0.01887 0.01053 -0.1463 0.7418 0.0837
-2.500 0.4461 0.01846 0.01011 -0.1458 0.7344 0.0883
-2.250 0.4769 0.01788 0.00948 -0.1461 0.7292 0.0945
-2.000 0.4996 0.01761 0.00923 -0.1450 0.7217 0.1030
-1.750 0.5258 0.01717 0.00883 -0.1446 0.7150 0.1149
-1.500 0.5557 0.01662 0.00831 -0.1449 0.7099 0.1304
-1.250 0.5775 0.01637 0.00817 -0.1438 0.7020 0.1457
-1.000 0.6044 0.01603 0.00789 -0.1436 0.6953 0.1645
-0.750 0.6344 0.01573 0.00760 -0.1439 0.6898 0.1917
-0.500 0.6555 0.01546 0.00765 -0.1427 0.6812 0.2452
-0.250 0.6806 0.01473 0.00753 -0.1424 0.6749 0.4224
0.000 0.6955 0.01390 0.00775 -0.1393 0.6686 0.7418
0.250 0.7212 0.01364 0.00777 -0.1378 0.6607 0.8929
0.500 0.7867 0.01352 0.00746 -0.1451 0.6539 1.0000
0.750 0.8052 0.01365 0.00753 -0.1433 0.6449 1.0000
1.000 0.8312 0.01368 0.00740 -0.1429 0.6375 1.0000
1.250 0.8538 0.01381 0.00743 -0.1419 0.6293 1.0000
1.500 0.8779 0.01390 0.00741 -0.1411 0.6212 1.0000
1.750 0.9035 0.01403 0.00740 -0.1406 0.6136 1.0000
2.000 0.9256 0.01417 0.00747 -0.1396 0.6047 1.0000
2.250 0.9530 0.01429 0.00744 -0.1394 0.5973 1.0000
2.500 0.9734 0.01447 0.00758 -0.1380 0.5876 1.0000
2.750 1.0001 0.01461 0.00756 -0.1378 0.5792 1.0000
3.000 1.0196 0.01479 0.00772 -0.1362 0.5687 1.0000
3.250 1.0443 0.01498 0.00777 -0.1356 0.5595 1.0000
3.500 1.0646 0.01519 0.00792 -0.1342 0.5491 1.0000
3.750 1.0874 0.01542 0.00806 -0.1333 0.5396 1.0000
4.000 1.1086 0.01566 0.00822 -0.1322 0.5297 1.0000
4.250 1.1299 0.01594 0.00843 -0.1310 0.5202 1.0000
4.500 1.1511 0.01621 0.00860 -0.1299 0.5107 1.0000
4.750 1.1705 0.01653 0.00888 -0.1285 0.5010 1.0000
5.000 1.1915 0.01683 0.00907 -0.1273 0.4918 1.0000
5.250 1.2093 0.01717 0.00939 -0.1257 0.4825 1.0000
5.500 1.2290 0.01749 0.00963 -0.1243 0.4741 1.0000
5.750 1.2465 0.01786 0.00998 -0.1227 0.4659 1.0000
6.000 1.2642 0.01823 0.01030 -0.1210 0.4581 1.0000
6.250 1.2860 0.01863 0.01061 -0.1202 0.4513 1.0000
6.500 1.3017 0.01905 0.01107 -0.1183 0.4441 1.0000
6.750 1.3230 0.01945 0.01138 -0.1174 0.4379 1.0000
7.000 1.3421 0.01990 0.01183 -0.1162 0.4317 1.0000
7.250 1.3584 0.02036 0.01231 -0.1146 0.4255 1.0000
7.500 1.3800 0.02078 0.01265 -0.1138 0.4200 1.0000
7.750 1.3986 0.02127 0.01315 -0.1126 0.4145 1.0000
8.000 1.4133 0.02179 0.01371 -0.1108 0.4086 1.0000
8.250 1.4321 0.02225 0.01412 -0.1097 0.4030 1.0000
8.500 1.4511 0.02277 0.01462 -0.1087 0.3978 1.0000
8.750 1.4655 0.02335 0.01528 -0.1070 0.3930 1.0000
9.000 1.4827 0.02389 0.01584 -0.1057 0.3885 1.0000
9.250 1.5054 0.02435 0.01623 -0.1053 0.3843 1.0000
9.500 1.5230 0.02495 0.01687 -0.1042 0.3803 1.0000
9.750 1.5357 0.02564 0.01765 -0.1024 0.3760 1.0000
10.000 1.5508 0.02626 0.01833 -0.1010 0.3717 1.0000
10.250 1.5709 0.02678 0.01880 -0.1002 0.3675 1.0000
10.500 1.5893 0.02740 0.01944 -0.0994 0.3637 1.0000
10.750 1.5986 0.02826 0.02043 -0.0973 0.3596 1.0000
11.000 1.6089 0.02907 0.02131 -0.0955 0.3548 1.0000
11.250 1.6258 0.02967 0.02187 -0.0944 0.3501 1.0000
11.500 1.6365 0.03057 0.02282 -0.0927 0.3455 1.0000
11.750 1.6413 0.03170 0.02409 -0.0905 0.3406 1.0000
12.000 1.6510 0.03265 0.02509 -0.0889 0.3359 1.0000
12.250 1.6692 0.03324 0.02559 -0.0881 0.3307 1.0000
12.500 1.6675 0.03484 0.02739 -0.0855 0.3259 1.0000
12.750 1.6712 0.03621 0.02885 -0.0836 0.3205 1.0000
13.000 1.6831 0.03713 0.02976 -0.0824 0.3155 1.0000
13.250 1.6871 0.03864 0.03138 -0.0807 0.3108 1.0000
13.500 1.6883 0.04040 0.03329 -0.0790 0.3055 1.0000
13.750 1.6940 0.04185 0.03477 -0.0775 0.3000 1.0000
14.000 1.6967 0.04363 0.03664 -0.0761 0.2944 1.0000
14.250 1.6945 0.04592 0.03909 -0.0745 0.2878 1.0000
14.500 1.6979 0.04771 0.04083 -0.0733 0.2810 1.0000
14.750 1.6914 0.05067 0.04402 -0.0719 0.2729 1.0000
15.000 1.6874 0.05338 0.04675 -0.0707 0.2641 1.0000
15.250 1.6784 0.05686 0.05037 -0.0697 0.2528 1.0000
15.500 1.6669 0.06076 0.05435 -0.0688 0.2387 1.0000
15.750 1.6489 0.06551 0.05909 -0.0679 0.2204 1.0000
16.000 1.6245 0.07115 0.06468 -0.0672 0.1967 1.0000
16.250 1.5935 0.07777 0.07118 -0.0667 0.1778 1.0000
16.500 1.5655 0.08421 0.07755 -0.0664 0.1644 1.0000
16.750 1.5430 0.09006 0.08336 -0.0664 0.1550 1.0000
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