GOE 368 AIRFOIL (goe368-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 368 AIRFOIL (goe368-il) Reynolds number: 100,000 Max Cl/Cd: 50.21 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe368-il-100000-n5.txt Download as CSV file: xf-goe368-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 368 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3972 0.11117 0.10642 -0.0048 1.0000 0.0470
-8.750 -0.4026 0.10984 0.10518 -0.0092 1.0000 0.0488
-8.500 -0.4023 0.10749 0.10290 -0.0120 1.0000 0.0492
-8.000 -0.3939 0.09901 0.09456 -0.0133 1.0000 0.0502
-7.750 -0.3840 0.09494 0.09050 -0.0123 1.0000 0.0511
-7.500 -0.3784 0.09180 0.08741 -0.0126 1.0000 0.0517
-7.250 -0.3753 0.08866 0.08434 -0.0131 1.0000 0.0522
-6.750 -0.3669 0.07867 0.07439 -0.0182 1.0000 0.0261
-6.500 -0.3601 0.07488 0.07065 -0.0204 1.0000 0.0251
-6.250 -0.3518 0.07086 0.06668 -0.0232 1.0000 0.0241
-6.000 -0.3418 0.06653 0.06233 -0.0264 1.0000 0.0232
-5.750 -0.3296 0.06191 0.05771 -0.0299 1.0000 0.0224
-5.500 -0.3149 0.05655 0.05231 -0.0339 1.0000 0.0215
-5.250 -0.2970 0.05049 0.04615 -0.0383 1.0000 0.0206
-5.000 -0.2734 0.04029 0.03562 -0.0452 1.0000 0.0192
-4.750 -0.2483 0.03253 0.02713 -0.0492 1.0000 0.0186
-4.500 -0.2261 0.02870 0.02273 -0.0501 1.0000 0.0190
-4.250 -0.2043 0.02610 0.01974 -0.0501 1.0000 0.0206
-4.000 -0.1818 0.02393 0.01716 -0.0497 1.0000 0.0219
-3.750 -0.1484 0.02173 0.01450 -0.0511 0.9943 0.0227
-3.500 -0.1065 0.01986 0.01222 -0.0537 0.9812 0.0239
-3.250 -0.0666 0.01854 0.01060 -0.0559 0.9673 0.0260
-3.000 -0.0285 0.01734 0.00914 -0.0578 0.9509 0.0303
-2.750 0.0086 0.01631 0.00788 -0.0593 0.9313 0.0352
-2.500 0.0463 0.01494 0.00658 -0.0609 0.9112 0.0599
-2.250 0.0858 0.01573 0.00735 -0.0627 0.8857 0.1571
-2.000 0.1234 0.01653 0.00789 -0.0642 0.8600 0.1864
-1.750 0.1579 0.01610 0.00721 -0.0650 0.8353 0.1886
-1.500 0.1891 0.01578 0.00667 -0.0652 0.8104 0.1911
-1.250 0.2177 0.01555 0.00624 -0.0648 0.7855 0.1942
-1.000 0.2450 0.01536 0.00585 -0.0643 0.7597 0.1980
-0.750 0.2720 0.01519 0.00551 -0.0637 0.7334 0.2026
-0.500 0.2984 0.01503 0.00526 -0.0630 0.7064 0.2077
-0.250 0.3246 0.01494 0.00497 -0.0623 0.6787 0.2141
0.000 0.3504 0.01484 0.00473 -0.0615 0.6509 0.2197
0.250 0.3760 0.01481 0.00453 -0.0606 0.6238 0.2267
0.500 0.4015 0.01480 0.00438 -0.0598 0.5975 0.2341
0.750 0.4274 0.01481 0.00427 -0.0592 0.5713 0.2436
1.000 0.4533 0.01479 0.00421 -0.0587 0.5452 0.2545
1.250 0.4792 0.01479 0.00416 -0.0582 0.5186 0.2691
1.500 0.5049 0.01481 0.00413 -0.0576 0.4922 0.2885
1.750 0.5303 0.01481 0.00412 -0.0571 0.4681 0.3208
2.000 0.5611 0.01346 0.00413 -0.0574 0.4443 1.0000
2.250 0.5863 0.01377 0.00422 -0.0568 0.4246 1.0000
2.500 0.6117 0.01407 0.00435 -0.0562 0.4065 1.0000
2.750 0.6372 0.01438 0.00453 -0.0557 0.3899 1.0000
3.000 0.6626 0.01470 0.00477 -0.0552 0.3744 1.0000
3.250 0.6881 0.01502 0.00501 -0.0547 0.3595 1.0000
3.500 0.7134 0.01535 0.00527 -0.0542 0.3449 1.0000
3.750 0.7387 0.01569 0.00558 -0.0537 0.3306 1.0000
4.000 0.7639 0.01605 0.00590 -0.0532 0.3170 1.0000
4.250 0.7889 0.01642 0.00623 -0.0527 0.3047 1.0000
4.750 0.8392 0.01720 0.00706 -0.0517 0.2835 1.0000
5.000 0.8642 0.01763 0.00751 -0.0512 0.2751 1.0000
5.250 0.8891 0.01807 0.00800 -0.0507 0.2675 1.0000
5.500 0.9141 0.01851 0.00851 -0.0502 0.2590 1.0000
5.750 0.9377 0.01880 0.00883 -0.0496 0.2390 1.0000
6.000 0.9611 0.01914 0.00913 -0.0491 0.2134 1.0000
6.250 0.9845 0.01961 0.00955 -0.0486 0.1927 1.0000
6.500 1.0078 0.02017 0.01007 -0.0480 0.1671 1.0000
6.750 1.0309 0.02084 0.01071 -0.0473 0.1348 1.0000
7.250 1.0621 0.02468 0.01403 -0.0447 0.0205 1.0000
7.500 1.0819 0.02590 0.01551 -0.0436 0.0190 1.0000
7.750 1.1001 0.02730 0.01721 -0.0424 0.0179 1.0000
8.000 1.1148 0.02909 0.01934 -0.0410 0.0165 1.0000
8.250 1.1276 0.03090 0.02146 -0.0395 0.0155 1.0000
8.500 1.1399 0.03256 0.02339 -0.0380 0.0148 1.0000
8.750 1.1484 0.03442 0.02550 -0.0363 0.0146 1.0000
9.000 1.1535 0.03639 0.02769 -0.0344 0.0143 1.0000
9.250 1.1554 0.03842 0.02990 -0.0323 0.0141 1.0000
9.500 1.1527 0.04052 0.03215 -0.0299 0.0140 1.0000
9.750 1.1496 0.04283 0.03460 -0.0282 0.0139 1.0000
10.000 1.1466 0.04547 0.03736 -0.0271 0.0138 1.0000
10.250 1.1461 0.04817 0.04016 -0.0265 0.0137 1.0000
10.500 1.1485 0.05081 0.04288 -0.0259 0.0136 1.0000
10.750 1.1532 0.05334 0.04550 -0.0252 0.0134 1.0000
11.000 1.1582 0.05599 0.04836 -0.0247 0.0128 1.0000
11.250 1.1637 0.05874 0.05124 -0.0242 0.0124 1.0000
11.500 1.1672 0.06177 0.05440 -0.0242 0.0120 1.0000
11.750 1.1700 0.06503 0.05781 -0.0242 0.0117 1.0000
12.000 1.1711 0.06861 0.06156 -0.0246 0.0116 1.0000
12.250 1.1702 0.07254 0.06570 -0.0254 0.0115 1.0000
12.500 1.1664 0.07692 0.07029 -0.0267 0.0116 1.0000
12.750 1.1607 0.08165 0.07522 -0.0286 0.0116 1.0000
13.000 1.1530 0.08685 0.08063 -0.0309 0.0117 1.0000
13.250 1.1439 0.09244 0.08642 -0.0338 0.0118 1.0000
13.500 1.1333 0.09846 0.09264 -0.0371 0.0118 1.0000
13.750 1.1223 0.10474 0.09911 -0.0408 0.0119 1.0000
14.000 1.1106 0.11143 0.10598 -0.0448 0.0120 1.0000
14.250 1.0981 0.11866 0.11339 -0.0493 0.0121 1.0000
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Polar data table (+)
Polar graphs
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