GOE 575 AIRFOIL (goe575-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 575 AIRFOIL (goe575-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.33 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe575-il-1000000.txt Download as CSV file: xf-goe575-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 575 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0221 0.07818 0.07575 -0.0625 0.9996 0.0248
-16.500 -1.1945 0.04443 0.04139 -0.0880 0.9993 0.0243
-16.250 -1.2166 0.04040 0.03718 -0.0879 0.9988 0.0244
-16.000 -1.2271 0.03798 0.03463 -0.0860 0.9979 0.0246
-15.750 -1.2351 0.03596 0.03245 -0.0835 0.9968 0.0248
-15.500 -1.2240 0.03522 0.03162 -0.0821 0.9960 0.0251
-15.250 -1.2193 0.03415 0.03042 -0.0800 0.9953 0.0253
-15.000 -1.2169 0.03311 0.02924 -0.0776 0.9946 0.0255
-14.750 -1.2288 0.03185 0.02789 -0.0718 0.9941 0.0259
-14.500 -1.2324 0.03101 0.02703 -0.0665 0.9933 0.0262
-14.250 -1.2273 0.03009 0.02603 -0.0631 0.9904 0.0264
-14.000 -1.2036 0.03026 0.02623 -0.0625 0.9891 0.0268
-13.750 -1.1882 0.02977 0.02568 -0.0609 0.9876 0.0271
-13.500 -1.1631 0.02994 0.02583 -0.0606 0.9868 0.0276
-13.250 -1.1496 0.02934 0.02509 -0.0588 0.9859 0.0278
-13.000 -1.1462 0.02881 0.02453 -0.0539 0.9809 0.0283
-12.750 -1.1290 0.02837 0.02400 -0.0523 0.9788 0.0286
-12.500 -1.1092 0.02802 0.02356 -0.0510 0.9775 0.0290
-12.250 -1.0968 0.02744 0.02287 -0.0482 0.9731 0.0292
-12.000 -1.0875 0.02657 0.02187 -0.0449 0.9704 0.0296
-11.750 -1.0712 0.02569 0.02091 -0.0430 0.9688 0.0299
-11.500 -1.0449 0.02573 0.02098 -0.0429 0.9679 0.0306
-11.250 -1.0200 0.02541 0.02063 -0.0425 0.9672 0.0309
-11.000 -1.0126 0.02488 0.02004 -0.0383 0.9625 0.0312
-10.750 -0.9888 0.02484 0.01999 -0.0374 0.9602 0.0317
-10.500 -0.9638 0.02443 0.01951 -0.0369 0.9587 0.0323
-10.250 -0.9383 0.02378 0.01877 -0.0366 0.9576 0.0325
-10.000 -0.9096 0.02381 0.01874 -0.0368 0.9569 0.0333
-9.750 -0.9006 0.02315 0.01800 -0.0328 0.9526 0.0335
-9.500 -0.8805 0.02292 0.01769 -0.0311 0.9499 0.0338
-9.250 -0.8591 0.02171 0.01638 -0.0300 0.9485 0.0346
-9.000 -0.8324 0.02114 0.01578 -0.0299 0.9474 0.0350
-8.750 -0.8031 0.02082 0.01545 -0.0302 0.9466 0.0355
-8.500 -0.7725 0.02055 0.01516 -0.0307 0.9460 0.0360
-8.250 -0.7615 0.02027 0.01485 -0.0270 0.9411 0.0365
-8.000 -0.7370 0.01984 0.01437 -0.0261 0.9386 0.0370
-7.750 -0.7091 0.01946 0.01394 -0.0260 0.9372 0.0376
-7.500 -0.6784 0.01908 0.01351 -0.0265 0.9361 0.0382
-7.250 -0.6481 0.01863 0.01300 -0.0269 0.9353 0.0386
-7.000 -0.6159 0.01822 0.01255 -0.0277 0.9346 0.0388
-6.750 -0.5833 0.01726 0.01154 -0.0288 0.9341 0.0397
-6.500 -0.5747 0.01685 0.01111 -0.0245 0.9281 0.0400
-6.250 -0.5475 0.01648 0.01076 -0.0242 0.9262 0.0409
-6.000 -0.5153 0.01604 0.01031 -0.0250 0.9247 0.0414
-5.750 -0.4826 0.01560 0.00986 -0.0258 0.9237 0.0422
-5.500 -0.4472 0.01515 0.00939 -0.0273 0.9228 0.0430
-5.250 -0.4094 0.01463 0.00886 -0.0292 0.9219 0.0436
-5.000 -0.3910 0.01427 0.00848 -0.0268 0.9160 0.0439
-4.750 -0.3609 0.01395 0.00814 -0.0270 0.9129 0.0445
-4.500 -0.3261 0.01319 0.00737 -0.0284 0.9113 0.0456
-4.250 -0.2909 0.01262 0.00681 -0.0298 0.9097 0.0464
-4.000 -0.2566 0.01216 0.00636 -0.0310 0.9086 0.0472
-3.750 -0.2318 0.01184 0.00604 -0.0301 0.9038 0.0482
-3.500 -0.2049 0.01152 0.00572 -0.0297 0.8986 0.0488
-3.250 -0.1691 0.01111 0.00530 -0.0312 0.8950 0.0497
-3.000 -0.1284 0.01072 0.00491 -0.0338 0.8927 0.0508
-2.750 -0.1060 0.01051 0.00469 -0.0324 0.8814 0.0511
-2.500 -0.0563 0.00993 0.00410 -0.0371 0.8770 0.0528
-2.250 -0.0162 0.00953 0.00369 -0.0396 0.8619 0.0548
-2.000 0.0328 0.00917 0.00327 -0.0442 0.8395 0.0564
-1.750 0.0859 0.00893 0.00284 -0.0497 0.7917 0.0585
-1.500 0.1049 0.00905 0.00272 -0.0475 0.7384 0.0615
-1.250 0.1236 0.00910 0.00266 -0.0453 0.7103 0.0653
-1.000 0.1448 0.00905 0.00263 -0.0438 0.6888 0.0887
-0.750 0.1668 0.00901 0.00263 -0.0424 0.6706 0.1179
-0.500 0.1869 0.00905 0.00265 -0.0406 0.6499 0.1346
0.000 0.2284 0.00915 0.00268 -0.0373 0.6106 0.1570
0.250 0.2489 0.00921 0.00271 -0.0356 0.5870 0.1700
0.500 0.2709 0.00926 0.00273 -0.0342 0.5695 0.1808
0.750 0.2923 0.00933 0.00276 -0.0328 0.5483 0.1954
1.000 0.3144 0.00939 0.00279 -0.0314 0.5290 0.2089
1.250 0.3371 0.00945 0.00282 -0.0303 0.5104 0.2246
1.500 0.3616 0.00944 0.00287 -0.0296 0.4911 0.2642
1.750 0.3935 0.00920 0.00297 -0.0309 0.4712 0.4061
2.000 0.5558 0.01012 0.00532 -0.0616 0.4286 0.9636
2.250 0.6086 0.01087 0.00596 -0.0670 0.4088 0.9734
2.500 0.6906 0.01127 0.00621 -0.0791 0.3871 0.9809
2.750 0.7626 0.01129 0.00612 -0.0890 0.3700 0.9883
3.000 0.8147 0.01135 0.00607 -0.0944 0.3535 0.9948
3.250 0.8734 0.01092 0.00554 -0.1015 0.3393 0.9999
3.500 0.8962 0.01100 0.00558 -0.1004 0.3309 1.0000
3.750 0.9174 0.01113 0.00566 -0.0990 0.3216 1.0000
4.000 0.9386 0.01125 0.00574 -0.0977 0.3127 1.0000
4.250 0.9597 0.01137 0.00583 -0.0963 0.3059 1.0000
4.500 0.9811 0.01148 0.00592 -0.0949 0.2986 1.0000
4.750 1.0015 0.01164 0.00603 -0.0934 0.2903 1.0000
5.000 1.0224 0.01175 0.00613 -0.0920 0.2819 1.0000
5.250 1.0423 0.01193 0.00625 -0.0903 0.2722 1.0000
5.500 1.0629 0.01206 0.00637 -0.0888 0.2649 1.0000
5.750 1.0824 0.01226 0.00651 -0.0872 0.2523 1.0000
6.000 1.1015 0.01249 0.00667 -0.0854 0.2393 1.0000
6.250 1.1209 0.01269 0.00683 -0.0838 0.2276 1.0000
6.500 1.1398 0.01292 0.00701 -0.0820 0.2148 1.0000
6.750 1.1581 0.01319 0.00722 -0.0801 0.2021 1.0000
7.000 1.1758 0.01349 0.00744 -0.0782 0.1896 1.0000
7.250 1.1935 0.01378 0.00768 -0.0762 0.1802 1.0000
7.500 1.2121 0.01400 0.00790 -0.0744 0.1747 1.0000
7.750 1.2303 0.01424 0.00812 -0.0726 0.1693 1.0000
8.000 1.2472 0.01455 0.00840 -0.0705 0.1624 1.0000
8.250 1.2655 0.01476 0.00863 -0.0687 0.1589 1.0000
8.500 1.2828 0.01501 0.00888 -0.0667 0.1545 1.0000
8.750 1.2992 0.01532 0.00918 -0.0645 0.1494 1.0000
9.000 1.3166 0.01558 0.00945 -0.0626 0.1454 1.0000
9.250 1.3337 0.01585 0.00972 -0.0606 0.1395 1.0000
9.500 1.3493 0.01621 0.01006 -0.0585 0.1332 1.0000
9.750 1.3660 0.01651 0.01036 -0.0564 0.1257 1.0000
10.000 1.3791 0.01697 0.01075 -0.0539 0.1138 1.0000
10.250 1.3891 0.01758 0.01126 -0.0508 0.0979 1.0000
10.500 1.3961 0.01836 0.01192 -0.0472 0.0810 1.0000
10.750 1.4065 0.01895 0.01248 -0.0443 0.0748 1.0000
11.000 1.4164 0.01956 0.01308 -0.0412 0.0700 1.0000
11.250 1.4277 0.02010 0.01363 -0.0386 0.0679 1.0000
11.500 1.4382 0.02069 0.01424 -0.0357 0.0651 1.0000
11.750 1.4508 0.02116 0.01476 -0.0333 0.0638 1.0000
12.000 1.4622 0.02171 0.01536 -0.0308 0.0628 1.0000
12.250 1.4719 0.02235 0.01602 -0.0281 0.0617 1.0000
12.500 1.4820 0.02299 0.01670 -0.0254 0.0604 1.0000
12.750 1.4895 0.02378 0.01752 -0.0225 0.0591 1.0000
13.000 1.4958 0.02466 0.01845 -0.0195 0.0579 1.0000
13.250 1.5028 0.02552 0.01938 -0.0167 0.0572 1.0000
13.500 1.5146 0.02614 0.02005 -0.0147 0.0566 1.0000
13.750 1.5231 0.02696 0.02093 -0.0123 0.0563 1.0000
14.000 1.5304 0.02788 0.02192 -0.0099 0.0558 1.0000
14.250 1.5395 0.02874 0.02283 -0.0078 0.0545 1.0000
14.500 1.5461 0.02978 0.02392 -0.0055 0.0538 1.0000
14.750 1.5511 0.03098 0.02517 -0.0032 0.0532 1.0000
15.000 1.5553 0.03228 0.02653 -0.0009 0.0528 1.0000
15.250 1.5580 0.03375 0.02804 0.0012 0.0511 1.0000
15.500 1.5569 0.03561 0.02998 0.0035 0.0507 1.0000
15.750 1.5559 0.03756 0.03200 0.0055 0.0498 1.0000
16.000 1.5582 0.03935 0.03388 0.0070 0.0497 1.0000
16.250 1.5656 0.04074 0.03534 0.0081 0.0491 1.0000
16.500 1.5727 0.04220 0.03687 0.0091 0.0483 1.0000
16.750 1.5755 0.04411 0.03886 0.0101 0.0479 1.0000
17.000 1.5763 0.04628 0.04110 0.0110 0.0471 1.0000
17.250 1.5753 0.04870 0.04360 0.0118 0.0465 1.0000
17.500 1.5758 0.05104 0.04597 0.0124 0.0453 1.0000
17.750 1.5743 0.05364 0.04866 0.0129 0.0447 1.0000
18.000 1.5640 0.05734 0.05243 0.0132 0.0437 1.0000
18.250 1.5595 0.06043 0.05561 0.0133 0.0430 1.0000
18.500 1.5613 0.06283 0.05810 0.0134 0.0424 1.0000
18.750 1.5587 0.06579 0.06115 0.0133 0.0416 1.0000
19.000 1.5537 0.06912 0.06457 0.0131 0.0409 1.0000
19.250 1.5473 0.07269 0.06820 0.0126 0.0397 1.0000
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