GOE 600 AIRFOIL (goe600-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 600 AIRFOIL (goe600-il) Reynolds number: 50,000 Max Cl/Cd: 33.9 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe600-il-50000-n5.txt Download as CSV file: xf-goe600-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 600 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5704 0.09615 0.08898 -0.0360 1.0000 0.0624
-11.000 -0.5940 0.08603 0.07891 -0.0425 1.0000 0.0619
-10.750 -0.6282 0.07558 0.06844 -0.0503 1.0000 0.0606
-10.500 -0.6654 0.06749 0.06023 -0.0556 1.0000 0.0593
-10.250 -0.6950 0.06240 0.05497 -0.0560 1.0000 0.0589
-10.000 -0.7121 0.05827 0.05062 -0.0553 1.0000 0.0595
-9.750 -0.7228 0.05446 0.04653 -0.0540 1.0000 0.0607
-9.500 -0.7290 0.05076 0.04247 -0.0524 1.0000 0.0621
-9.250 -0.7313 0.04717 0.03843 -0.0505 1.0000 0.0640
-9.000 -0.7272 0.04440 0.03535 -0.0486 1.0000 0.0667
-8.750 -0.7161 0.04304 0.03401 -0.0469 1.0000 0.0702
-8.500 -0.7074 0.04093 0.03162 -0.0449 1.0000 0.0741
-8.250 -0.6975 0.03877 0.02913 -0.0429 1.0000 0.0783
-8.000 -0.6852 0.03775 0.02813 -0.0411 1.0000 0.0832
-7.750 -0.6731 0.03601 0.02592 -0.0390 1.0000 0.0894
-7.500 -0.6600 0.03508 0.02510 -0.0372 1.0000 0.0951
-7.250 -0.6461 0.03373 0.02335 -0.0353 1.0000 0.1025
-7.000 -0.6319 0.03271 0.02243 -0.0336 1.0000 0.1090
-6.750 -0.6168 0.03161 0.02107 -0.0318 1.0000 0.1182
-6.500 -0.6015 0.03057 0.02006 -0.0301 1.0000 0.1261
-6.250 -0.5857 0.02956 0.01892 -0.0285 1.0000 0.1369
-6.000 -0.5698 0.02864 0.01789 -0.0269 1.0000 0.1502
-5.750 -0.5535 0.02772 0.01693 -0.0255 1.0000 0.1646
-5.500 -0.5375 0.02686 0.01614 -0.0241 1.0000 0.1816
-5.250 -0.5085 0.02597 0.01533 -0.0254 0.9954 0.2060
-5.000 -0.4754 0.02520 0.01462 -0.0273 0.9889 0.2362
-4.750 -0.4420 0.02453 0.01414 -0.0294 0.9826 0.2813
-4.500 -0.4104 0.02392 0.01381 -0.0310 0.9758 0.3409
-4.250 -0.3800 0.02349 0.01359 -0.0320 0.9690 0.4056
-4.000 -0.3483 0.02328 0.01349 -0.0330 0.9625 0.4628
-3.750 -0.3181 0.02319 0.01339 -0.0335 0.9555 0.5080
-3.500 -0.2863 0.02316 0.01328 -0.0344 0.9490 0.5502
-3.250 -0.2559 0.02314 0.01324 -0.0350 0.9426 0.5863
-3.000 -0.2265 0.02313 0.01319 -0.0353 0.9357 0.6185
-2.750 -0.1925 0.02314 0.01317 -0.0363 0.9308 0.6542
-2.500 -0.1691 0.02318 0.01324 -0.0352 0.9230 0.6892
-2.250 -0.1390 0.02323 0.01335 -0.0351 0.9175 0.7275
-2.000 -0.1118 0.02333 0.01347 -0.0344 0.9114 0.7639
-1.750 -0.0846 0.02343 0.01359 -0.0338 0.9048 0.7986
-1.500 -0.0485 0.02352 0.01365 -0.0349 0.9004 0.8317
-1.250 -0.0176 0.02367 0.01377 -0.0355 0.8937 0.8612
-1.000 0.0236 0.02380 0.01383 -0.0381 0.8884 0.8901
-0.750 0.0739 0.02391 0.01384 -0.0426 0.8847 0.9183
-0.500 0.1191 0.02409 0.01394 -0.0466 0.8782 0.9473
-0.250 0.1747 0.02415 0.01391 -0.0525 0.8729 0.9732
0.000 0.2355 0.02407 0.01374 -0.0595 0.8670 0.9953
0.250 0.2629 0.02401 0.01359 -0.0603 0.8561 1.0000
0.500 0.2802 0.02407 0.01356 -0.0590 0.8441 1.0000
0.750 0.3020 0.02414 0.01355 -0.0583 0.8338 1.0000
1.000 0.3293 0.02416 0.01350 -0.0584 0.8252 1.0000
1.250 0.3474 0.02439 0.01367 -0.0570 0.8140 1.0000
1.500 0.3720 0.02452 0.01376 -0.0566 0.8045 1.0000
1.750 0.3995 0.02458 0.01379 -0.0564 0.7954 1.0000
2.000 0.4204 0.02481 0.01401 -0.0553 0.7841 1.0000
2.250 0.4472 0.02489 0.01410 -0.0550 0.7743 1.0000
2.500 0.4753 0.02491 0.01413 -0.0547 0.7645 1.0000
2.750 0.4977 0.02511 0.01436 -0.0537 0.7523 1.0000
3.000 0.5231 0.02521 0.01449 -0.0530 0.7408 1.0000
3.250 0.5539 0.02508 0.01440 -0.0529 0.7307 1.0000
3.500 0.5786 0.02517 0.01455 -0.0519 0.7176 1.0000
3.750 0.6026 0.02526 0.01470 -0.0509 0.7036 1.0000
4.000 0.6274 0.02532 0.01483 -0.0499 0.6891 1.0000
4.250 0.6523 0.02534 0.01493 -0.0489 0.6739 1.0000
4.500 0.6773 0.02533 0.01500 -0.0478 0.6577 1.0000
4.750 0.7024 0.02530 0.01504 -0.0466 0.6407 1.0000
5.000 0.7277 0.02523 0.01506 -0.0455 0.6230 1.0000
5.250 0.7482 0.02540 0.01533 -0.0439 0.6021 1.0000
5.500 0.7707 0.02547 0.01549 -0.0425 0.5810 1.0000
5.750 0.7946 0.02548 0.01557 -0.0412 0.5600 1.0000
6.000 0.8155 0.02569 0.01587 -0.0397 0.5360 1.0000
6.250 0.8384 0.02580 0.01603 -0.0384 0.5121 1.0000
6.500 0.8615 0.02590 0.01609 -0.0369 0.4862 1.0000
6.750 0.8822 0.02615 0.01629 -0.0352 0.4570 1.0000
7.000 0.9014 0.02659 0.01661 -0.0335 0.4272 1.0000
7.250 0.9191 0.02723 0.01716 -0.0317 0.3986 1.0000
7.500 0.9365 0.02798 0.01788 -0.0301 0.3733 1.0000
7.750 0.9538 0.02880 0.01873 -0.0286 0.3505 1.0000
8.000 0.9698 0.02969 0.01965 -0.0270 0.3280 1.0000
8.250 0.9842 0.03063 0.02062 -0.0252 0.3054 1.0000
8.500 0.9980 0.03163 0.02161 -0.0234 0.2843 1.0000
8.750 1.0112 0.03272 0.02277 -0.0216 0.2638 1.0000
9.000 1.0214 0.03387 0.02389 -0.0195 0.2432 1.0000
9.250 1.0268 0.03511 0.02515 -0.0169 0.2218 1.0000
9.500 1.0294 0.03648 0.02647 -0.0143 0.2011 1.0000
9.750 1.0321 0.03801 0.02790 -0.0121 0.1826 1.0000
10.000 1.0374 0.03967 0.02961 -0.0103 0.1654 1.0000
10.250 1.0426 0.04145 0.03142 -0.0087 0.1503 1.0000
10.500 1.0475 0.04337 0.03338 -0.0071 0.1366 1.0000
10.750 1.0511 0.04546 0.03548 -0.0057 0.1239 1.0000
11.000 1.0535 0.04770 0.03774 -0.0045 0.1124 1.0000
11.250 1.0570 0.05006 0.04022 -0.0033 0.1017 1.0000
11.500 1.0612 0.05251 0.04276 -0.0022 0.0932 1.0000
11.750 1.0637 0.05496 0.04514 -0.0013 0.0866 1.0000
12.000 1.0682 0.05767 0.04811 -0.0004 0.0798 1.0000
12.250 1.0721 0.06022 0.05068 0.0004 0.0750 1.0000
12.500 1.0750 0.06318 0.05382 0.0010 0.0706 1.0000
12.750 1.0743 0.06651 0.05743 0.0014 0.0667 1.0000
13.000 1.0743 0.06964 0.06068 0.0016 0.0636 1.0000
13.250 1.0783 0.07247 0.06348 0.0020 0.0610 1.0000
13.500 1.0690 0.07718 0.06858 0.0014 0.0593 1.0000
13.750 1.0571 0.08230 0.07401 0.0003 0.0578 1.0000
14.000 1.0430 0.08792 0.07990 -0.0015 0.0566 1.0000
14.250 1.0261 0.09422 0.08644 -0.0040 0.0557 1.0000
14.500 1.0050 0.10176 0.09421 -0.0075 0.0554 1.0000
14.750 0.9757 0.11180 0.10451 -0.0130 0.0559 1.0000
15.000 0.9351 0.12591 0.11882 -0.0214 0.0573 1.0000
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