GOE 393 AIRFOIL (goe393-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 393 AIRFOIL (goe393-il) Reynolds number: 200,000 Max Cl/Cd: 75.36 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe393-il-200000.txt Download as CSV file: xf-goe393-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 393 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4780 0.11111 0.10767 0.0187 1.0000 0.0390
-8.500 -0.4765 0.10937 0.10597 0.0134 1.0000 0.0403
-8.250 -0.4765 0.10739 0.10406 0.0076 1.0000 0.0406
-8.000 -0.4673 0.10405 0.10073 0.0011 1.0000 0.0408
-7.750 -0.4606 0.09768 0.09439 0.0071 1.0000 0.0416
-7.500 -0.4498 0.09403 0.09074 0.0082 1.0000 0.0425
-7.250 -0.4399 0.09086 0.08759 0.0069 1.0000 0.0437
-7.000 -0.4285 0.08758 0.08432 0.0043 1.0000 0.0452
-6.750 -0.4149 0.08412 0.08088 0.0003 1.0000 0.0476
-6.500 -0.3757 0.08087 0.07747 -0.0204 1.0000 0.0506
-6.250 -0.3739 0.07525 0.07195 -0.0165 1.0000 0.0514
-6.000 -0.3628 0.07198 0.06871 -0.0148 1.0000 0.0525
-5.750 -0.3465 0.06891 0.06565 -0.0160 1.0000 0.0541
-5.500 -0.3259 0.06563 0.06234 -0.0191 1.0000 0.0568
-5.000 -0.2690 0.05725 0.05377 -0.0313 1.0000 0.0629
-4.750 -0.2525 0.05453 0.05108 -0.0311 1.0000 0.0645
-4.500 -0.2301 0.05176 0.04830 -0.0327 1.0000 0.0671
-4.250 -0.1773 0.04938 0.04537 -0.0417 1.0000 0.0735
-4.000 -0.1663 0.04465 0.04085 -0.0413 0.9992 0.0747
-3.750 -0.1261 0.04140 0.03760 -0.0458 0.9579 0.0776
-3.500 -0.0723 0.03985 0.03546 -0.0514 0.8948 0.0862
-3.250 -0.0488 0.03580 0.03107 -0.0519 0.8413 0.0874
-2.750 -0.0076 0.03167 0.02658 -0.0506 0.7787 0.0907
-2.500 0.0280 0.03189 0.02610 -0.0509 0.7586 0.1003
-2.250 0.0572 0.02412 0.01773 -0.0520 0.7452 0.0746
-2.000 0.0839 0.02207 0.01545 -0.0518 0.7301 0.0697
-1.750 0.1129 0.01938 0.01225 -0.0517 0.7169 0.0669
-1.500 0.1411 0.01791 0.01040 -0.0514 0.7040 0.0684
-1.250 0.1694 0.01665 0.00878 -0.0511 0.6919 0.0704
-1.000 0.1974 0.01557 0.00735 -0.0506 0.6809 0.0722
-0.750 0.2250 0.01471 0.00630 -0.0502 0.6701 0.0754
-0.500 0.2527 0.01441 0.00596 -0.0500 0.6589 0.0806
-0.250 0.2803 0.01399 0.00543 -0.0496 0.6485 0.0897
0.000 0.3076 0.01388 0.00525 -0.0492 0.6387 0.1064
0.250 0.3351 0.01368 0.00502 -0.0490 0.6275 0.1238
0.500 0.3624 0.01349 0.00480 -0.0487 0.6175 0.1344
0.750 0.3896 0.01343 0.00466 -0.0484 0.6084 0.1450
1.000 0.4171 0.01340 0.00465 -0.0482 0.5976 0.1579
1.250 0.4442 0.01320 0.00452 -0.0480 0.5877 0.1669
1.500 0.4714 0.01313 0.00436 -0.0476 0.5783 0.1711
1.750 0.4986 0.01293 0.00425 -0.0473 0.5674 0.1760
2.000 0.5259 0.01287 0.00422 -0.0470 0.5576 0.1828
2.250 0.5529 0.01281 0.00417 -0.0467 0.5484 0.1927
2.500 0.5803 0.01276 0.00421 -0.0465 0.5379 0.2071
2.750 0.6073 0.01266 0.00427 -0.0462 0.5288 0.2536
3.000 0.6384 0.01126 0.00426 -0.0466 0.5191 1.0000
3.250 0.6657 0.01143 0.00436 -0.0462 0.5082 1.0000
3.500 0.6927 0.01160 0.00445 -0.0459 0.4980 1.0000
3.750 0.7196 0.01177 0.00452 -0.0455 0.4877 1.0000
4.000 0.7466 0.01187 0.00463 -0.0452 0.4753 1.0000
4.250 0.7735 0.01200 0.00474 -0.0448 0.4633 1.0000
4.500 0.8003 0.01217 0.00489 -0.0445 0.4533 1.0000
4.750 0.8271 0.01235 0.00505 -0.0442 0.4437 1.0000
5.000 0.8540 0.01249 0.00525 -0.0439 0.4323 1.0000
5.250 0.8807 0.01267 0.00545 -0.0436 0.4217 1.0000
5.500 0.9073 0.01288 0.00566 -0.0432 0.4126 1.0000
5.750 0.9341 0.01305 0.00592 -0.0429 0.4018 1.0000
6.000 0.9606 0.01325 0.00619 -0.0426 0.3906 1.0000
6.250 0.9869 0.01345 0.00644 -0.0422 0.3781 1.0000
6.500 1.0127 0.01360 0.00666 -0.0418 0.3597 1.0000
6.750 1.0380 0.01378 0.00685 -0.0413 0.3332 1.0000
7.000 1.0626 0.01410 0.00710 -0.0409 0.2964 1.0000
7.250 1.0861 0.01468 0.00749 -0.0404 0.2288 1.0000
7.500 1.1059 0.01602 0.00840 -0.0399 0.1649 1.0000
7.750 1.1270 0.01714 0.00939 -0.0394 0.1392 1.0000
8.000 1.1492 0.01804 0.01028 -0.0389 0.1178 1.0000
8.250 1.1700 0.01913 0.01130 -0.0383 0.0925 1.0000
8.500 1.1878 0.02069 0.01270 -0.0374 0.0634 1.0000
8.750 1.2050 0.02224 0.01419 -0.0364 0.0504 1.0000
9.000 1.2240 0.02345 0.01550 -0.0354 0.0445 1.0000
9.250 1.2372 0.02535 0.01737 -0.0340 0.0403 1.0000
9.500 1.2549 0.02659 0.01876 -0.0329 0.0372 1.0000
9.750 1.2701 0.02809 0.02032 -0.0317 0.0349 1.0000
10.000 1.2826 0.03000 0.02226 -0.0302 0.0331 1.0000
10.250 1.2941 0.03266 0.02500 -0.0285 0.0317 1.0000
10.500 1.3096 0.03431 0.02686 -0.0272 0.0308 1.0000
10.750 1.3234 0.03609 0.02882 -0.0259 0.0294 1.0000
11.000 1.3358 0.03793 0.03081 -0.0246 0.0281 1.0000
11.250 1.3462 0.04005 0.03309 -0.0232 0.0272 1.0000
11.500 1.3542 0.04239 0.03560 -0.0217 0.0265 1.0000
11.750 1.3596 0.04496 0.03836 -0.0201 0.0260 1.0000
12.000 1.3621 0.04793 0.04152 -0.0186 0.0257 1.0000
12.250 1.3603 0.05128 0.04509 -0.0173 0.0254 1.0000
12.500 1.3545 0.05492 0.04898 -0.0164 0.0253 1.0000
12.750 1.3455 0.05886 0.05318 -0.0162 0.0253 1.0000
13.000 1.3338 0.06320 0.05778 -0.0169 0.0253 1.0000
13.250 1.3201 0.06796 0.06279 -0.0183 0.0254 1.0000
13.500 1.3042 0.07326 0.06833 -0.0204 0.0254 1.0000
13.750 1.2853 0.07923 0.07455 -0.0234 0.0256 1.0000
14.000 1.2607 0.08657 0.08218 -0.0276 0.0260 1.0000
14.250 1.2211 0.09729 0.09326 -0.0346 0.0267 1.0000
14.500 1.1742 0.11077 0.10703 -0.0439 0.0276 1.0000
14.750 1.1258 0.12711 0.12360 -0.0549 0.0287 1.0000
15.000 1.0707 0.14877 0.14535 -0.0682 0.0306 1.0000
15.250 1.0531 0.15954 0.15607 -0.0732 0.0316 1.0000
15.500 0.8552 0.14252 0.13928 -0.0465 0.0328 1.0000
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Polar data table (+)
Polar graphs
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