GOE 395 AIRFOIL (goe395-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 395 AIRFOIL (goe395-il) Reynolds number: 200,000 Max Cl/Cd: 102.82 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe395-il-200000.txt Download as CSV file: xf-goe395-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 395 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1741 0.09469 0.09124 -0.0537 0.9230 0.0386
-7.750 -0.1644 0.09229 0.08882 -0.0556 0.9148 0.0407
-7.500 -0.1551 0.09157 0.08808 -0.0615 0.9062 0.0423
-7.250 -0.1351 0.09004 0.08651 -0.0718 0.8992 0.0427
-7.000 -0.1273 0.08490 0.08137 -0.0700 0.8962 0.0432
-6.750 -0.1170 0.08114 0.07760 -0.0673 0.8932 0.0441
-6.500 -0.1021 0.07839 0.07484 -0.0685 0.8894 0.0454
-6.250 -0.0849 0.07578 0.07221 -0.0712 0.8858 0.0474
-6.000 -0.0412 0.07416 0.07047 -0.0877 0.8815 0.0524
-5.750 -0.0162 0.06973 0.06601 -0.0942 0.8781 0.0531
-5.500 -0.0093 0.06630 0.06260 -0.0906 0.8754 0.0539
-5.250 0.0068 0.06368 0.05998 -0.0906 0.8728 0.0553
-5.000 0.0298 0.06116 0.05742 -0.0936 0.8703 0.0577
-4.750 0.1056 0.05789 0.05389 -0.1161 0.8677 0.0641
-4.500 0.1118 0.05415 0.05017 -0.1130 0.8660 0.0650
-4.250 0.1282 0.05179 0.04783 -0.1124 0.8639 0.0663
-4.000 0.1529 0.04958 0.04560 -0.1145 0.8612 0.0686
-3.750 0.2317 0.04609 0.04171 -0.1333 0.8587 0.0769
-3.500 0.2451 0.04287 0.03857 -0.1322 0.8568 0.0780
-3.250 0.2661 0.04091 0.03660 -0.1323 0.8546 0.0795
-3.000 0.2933 0.03898 0.03460 -0.1338 0.8519 0.0821
-2.500 0.3736 0.03354 0.02878 -0.1440 0.8437 0.0929
-2.250 0.3997 0.03198 0.02717 -0.1447 0.8400 0.0953
-2.000 0.4327 0.03019 0.02521 -0.1466 0.8367 0.1004
-1.750 0.4882 0.02347 0.01757 -0.1536 0.8336 0.0745
-1.500 0.5213 0.02139 0.01510 -0.1552 0.8296 0.0751
-1.250 0.5529 0.01971 0.01299 -0.1560 0.8261 0.0759
-1.000 0.5830 0.01821 0.01114 -0.1564 0.8229 0.0782
-0.750 0.6108 0.01773 0.01059 -0.1562 0.8198 0.0824
-0.500 0.6391 0.01741 0.01008 -0.1563 0.8150 0.0900
-0.250 0.6664 0.01705 0.00973 -0.1561 0.8106 0.1008
0.000 0.6942 0.01662 0.00921 -0.1558 0.8069 0.1131
0.250 0.7215 0.01644 0.00898 -0.1555 0.8028 0.1244
0.500 0.7483 0.01641 0.00894 -0.1553 0.7975 0.1361
0.750 0.7753 0.01631 0.00884 -0.1549 0.7931 0.1470
1.000 0.8027 0.01602 0.00854 -0.1544 0.7894 0.1530
1.250 0.8291 0.01596 0.00855 -0.1541 0.7831 0.1582
1.500 0.8563 0.01578 0.00836 -0.1536 0.7781 0.1648
1.750 0.8834 0.01558 0.00822 -0.1531 0.7736 0.1722
2.000 0.9096 0.01553 0.00825 -0.1527 0.7665 0.1795
2.250 0.9369 0.01530 0.00808 -0.1521 0.7613 0.1905
2.500 0.9632 0.01522 0.00814 -0.1516 0.7544 0.2075
2.750 0.9900 0.01487 0.00804 -0.1510 0.7475 0.2656
3.000 1.0129 0.01371 0.00799 -0.1495 0.7399 1.0000
3.250 1.0397 0.01358 0.00777 -0.1486 0.7313 1.0000
3.500 1.0656 0.01355 0.00774 -0.1478 0.7213 1.0000
3.750 1.0931 0.01340 0.00752 -0.1471 0.7140 1.0000
4.000 1.1187 0.01335 0.00751 -0.1463 0.7024 1.0000
4.250 1.1448 0.01323 0.00741 -0.1455 0.6907 1.0000
4.500 1.1710 0.01307 0.00728 -0.1447 0.6784 1.0000
4.750 1.1969 0.01290 0.00714 -0.1439 0.6636 1.0000
5.000 1.2225 0.01274 0.00704 -0.1431 0.6452 1.0000
5.250 1.2477 0.01257 0.00692 -0.1422 0.6194 1.0000
5.500 1.2724 0.01245 0.00671 -0.1411 0.5845 1.0000
5.750 1.2955 0.01260 0.00663 -0.1398 0.5479 1.0000
6.000 1.3172 0.01309 0.00687 -0.1385 0.5148 1.0000
6.250 1.3393 0.01367 0.00733 -0.1374 0.4892 1.0000
6.500 1.3610 0.01426 0.00782 -0.1363 0.4647 1.0000
6.750 1.3822 0.01482 0.00834 -0.1352 0.4374 1.0000
7.000 1.4018 0.01547 0.00888 -0.1338 0.4050 1.0000
7.250 1.4202 0.01616 0.00947 -0.1324 0.3677 1.0000
7.500 1.4368 0.01698 0.01015 -0.1307 0.3273 1.0000
7.750 1.4507 0.01800 0.01096 -0.1287 0.2742 1.0000
8.000 1.4587 0.01951 0.01202 -0.1261 0.2038 1.0000
8.250 1.4662 0.02108 0.01325 -0.1234 0.1593 1.0000
8.500 1.4763 0.02237 0.01442 -0.1211 0.1350 1.0000
8.750 1.4848 0.02364 0.01561 -0.1185 0.1155 1.0000
9.000 1.4928 0.02489 0.01682 -0.1158 0.0901 1.0000
9.250 1.4927 0.02685 0.01851 -0.1124 0.0587 1.0000
9.500 1.4924 0.02893 0.02053 -0.1091 0.0458 1.0000
9.750 1.4922 0.03108 0.02269 -0.1061 0.0405 1.0000
10.000 1.4982 0.03278 0.02451 -0.1038 0.0369 1.0000
10.250 1.5019 0.03473 0.02652 -0.1016 0.0344 1.0000
10.500 1.4990 0.03738 0.02921 -0.0989 0.0325 1.0000
10.750 1.5057 0.03919 0.03115 -0.0970 0.0310 1.0000
11.000 1.5120 0.04107 0.03316 -0.0952 0.0293 1.0000
11.250 1.5173 0.04305 0.03522 -0.0935 0.0278 1.0000
11.500 1.5215 0.04520 0.03743 -0.0916 0.0268 1.0000
11.750 1.5252 0.04754 0.03982 -0.0895 0.0259 1.0000
12.000 1.5327 0.05010 0.04241 -0.0868 0.0251 1.0000
12.250 1.5419 0.05216 0.04466 -0.0851 0.0247 1.0000
12.500 1.5507 0.05442 0.04712 -0.0832 0.0242 1.0000
12.750 1.5578 0.05690 0.04983 -0.0815 0.0238 1.0000
13.000 1.5616 0.05959 0.05274 -0.0798 0.0232 1.0000
13.250 1.5628 0.06246 0.05583 -0.0783 0.0226 1.0000
13.500 1.5622 0.06549 0.05906 -0.0770 0.0220 1.0000
13.750 1.5599 0.06881 0.06259 -0.0757 0.0216 1.0000
14.000 1.5546 0.07266 0.06670 -0.0745 0.0215 1.0000
14.250 1.5458 0.07692 0.07122 -0.0736 0.0214 1.0000
14.500 1.5334 0.08167 0.07625 -0.0731 0.0214 1.0000
14.750 1.5175 0.08698 0.08184 -0.0730 0.0215 1.0000
15.000 1.4987 0.09287 0.08803 -0.0737 0.0216 1.0000
15.250 1.4783 0.09939 0.09482 -0.0752 0.0217 1.0000
15.500 1.4562 0.10665 0.10236 -0.0777 0.0219 1.0000
15.750 1.4331 0.11466 0.11064 -0.0814 0.0222 1.0000
16.000 1.4098 0.12342 0.11964 -0.0862 0.0224 1.0000
16.250 1.3859 0.13305 0.12950 -0.0920 0.0227 1.0000
16.500 1.3613 0.14372 0.14038 -0.0992 0.0230 1.0000
16.750 1.3356 0.15566 0.15250 -0.1076 0.0234 1.0000
17.000 1.3078 0.16963 0.16659 -0.1176 0.0240 1.0000
17.250 1.2835 0.18390 0.18092 -0.1271 0.0247 1.0000
17.500 0.9307 0.19265 0.18984 -0.1031 0.0423 1.0000
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