GOE 575 AIRFOIL (goe575-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 575 AIRFOIL (goe575-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.36 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe575-il-1000000-n5.txt Download as CSV file: xf-goe575-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.500 -1.2258 0.03671 0.03302 -0.1170 0.9807 0.0198
-17.250 -1.2341 0.03453 0.03074 -0.1150 0.9799 0.0200
-17.000 -1.2361 0.03289 0.02899 -0.1127 0.9792 0.0202
-16.750 -1.2280 0.03175 0.02781 -0.1113 0.9786 0.0209
-16.500 -1.2233 0.03051 0.02646 -0.1092 0.9780 0.0210
-16.250 -1.2117 0.02973 0.02562 -0.1075 0.9776 0.0218
-16.000 -1.2017 0.02886 0.02466 -0.1056 0.9772 0.0221
-15.750 -1.1895 0.02808 0.02379 -0.1039 0.9769 0.0225
-15.500 -1.2024 0.02721 0.02285 -0.0967 0.9729 0.0227
-15.250 -1.1929 0.02656 0.02211 -0.0939 0.9716 0.0230
-15.000 -1.1843 0.02576 0.02123 -0.0911 0.9705 0.0232
-14.750 -1.1688 0.02522 0.02065 -0.0893 0.9697 0.0237
-14.500 -1.1502 0.02480 0.02021 -0.0879 0.9691 0.0243
-14.250 -1.1330 0.02429 0.01963 -0.0864 0.9685 0.0246
-14.000 -1.1148 0.02378 0.01906 -0.0849 0.9680 0.0249
-13.750 -1.0920 0.02347 0.01871 -0.0842 0.9677 0.0256
-13.500 -1.0999 0.02294 0.01812 -0.0771 0.9629 0.0258
-13.250 -1.0835 0.02256 0.01767 -0.0750 0.9615 0.0263
-13.000 -1.0672 0.02207 0.01709 -0.0730 0.9604 0.0265
-12.750 -1.0476 0.02168 0.01665 -0.0715 0.9596 0.0270
-12.500 -1.0276 0.02126 0.01619 -0.0702 0.9589 0.0273
-12.250 -1.0070 0.02084 0.01573 -0.0689 0.9584 0.0275
-12.000 -0.9830 0.02061 0.01548 -0.0682 0.9580 0.0280
-11.750 -0.9892 0.02028 0.01510 -0.0610 0.9525 0.0282
-11.500 -0.9703 0.02000 0.01478 -0.0592 0.9510 0.0286
-11.250 -0.9496 0.01965 0.01439 -0.0577 0.9500 0.0290
-11.000 -0.9263 0.01938 0.01408 -0.0568 0.9492 0.0295
-10.750 -0.9040 0.01894 0.01357 -0.0557 0.9485 0.0298
-10.500 -0.8779 0.01866 0.01324 -0.0553 0.9479 0.0303
-10.000 -0.8501 0.01798 0.01246 -0.0493 0.9410 0.0309
-9.750 -0.8279 0.01752 0.01196 -0.0481 0.9394 0.0311
-9.500 -0.8016 0.01729 0.01174 -0.0477 0.9384 0.0318
-9.250 -0.7755 0.01686 0.01127 -0.0473 0.9374 0.0321
-9.000 -0.7476 0.01666 0.01106 -0.0472 0.9368 0.0326
-8.750 -0.7195 0.01635 0.01072 -0.0472 0.9362 0.0332
-8.500 -0.7160 0.01613 0.01046 -0.0418 0.9301 0.0333
-8.250 -0.6918 0.01583 0.01013 -0.0409 0.9281 0.0337
-8.000 -0.6656 0.01544 0.00970 -0.0404 0.9266 0.0340
-7.750 -0.6373 0.01514 0.00937 -0.0404 0.9255 0.0345
-7.500 -0.6084 0.01482 0.00902 -0.0405 0.9245 0.0348
-7.250 -0.5792 0.01447 0.00864 -0.0406 0.9236 0.0350
-7.000 -0.5698 0.01428 0.00842 -0.0364 0.9175 0.0352
-6.750 -0.5452 0.01391 0.00804 -0.0356 0.9149 0.0359
-6.500 -0.5177 0.01352 0.00763 -0.0353 0.9127 0.0361
-6.250 -0.4895 0.01321 0.00731 -0.0352 0.9111 0.0366
-6.000 -0.4591 0.01288 0.00698 -0.0356 0.9096 0.0371
-5.750 -0.4446 0.01276 0.00684 -0.0325 0.9028 0.0375
-5.500 -0.4163 0.01244 0.00650 -0.0323 0.8978 0.0381
-5.250 -0.3820 0.01209 0.00614 -0.0335 0.8952 0.0388
-5.000 -0.3551 0.01181 0.00583 -0.0331 0.8852 0.0390
-4.750 -0.3149 0.01142 0.00541 -0.0356 0.8791 0.0396
-4.500 -0.2754 0.01110 0.00507 -0.0381 0.8699 0.0400
-4.250 -0.2235 0.01057 0.00451 -0.0433 0.8595 0.0408
-4.000 -0.1605 0.01011 0.00396 -0.0511 0.8268 0.0418
-3.750 -0.1267 0.01007 0.00367 -0.0523 0.7665 0.0424
-3.250 -0.0989 0.01032 0.00357 -0.0457 0.6919 0.0438
-3.000 -0.0771 0.01029 0.00348 -0.0443 0.6767 0.0443
-2.750 -0.0554 0.01028 0.00339 -0.0428 0.6601 0.0447
-2.500 -0.0338 0.01028 0.00333 -0.0413 0.6444 0.0454
-2.250 -0.0103 0.01023 0.00324 -0.0402 0.6300 0.0460
-2.000 0.0134 0.01017 0.00313 -0.0392 0.6149 0.0470
-1.750 0.0366 0.01015 0.00306 -0.0380 0.5996 0.0480
-1.500 0.0591 0.01015 0.00301 -0.0367 0.5834 0.0489
-1.250 0.0814 0.01016 0.00296 -0.0354 0.5655 0.0502
-1.000 0.1044 0.01018 0.00291 -0.0342 0.5507 0.0513
-0.750 0.1271 0.01021 0.00288 -0.0330 0.5330 0.0519
-0.500 0.1506 0.01022 0.00284 -0.0320 0.5175 0.0537
-0.250 0.1749 0.01022 0.00281 -0.0311 0.5023 0.0561
0.250 0.2213 0.01033 0.00278 -0.0291 0.4586 0.0663
0.500 0.2470 0.01028 0.00280 -0.0287 0.4389 0.1070
0.750 0.2712 0.01032 0.00282 -0.0279 0.4239 0.1174
1.000 0.2946 0.01041 0.00285 -0.0269 0.4053 0.1246
1.250 0.3190 0.01045 0.00289 -0.0261 0.3927 0.1353
1.500 0.3433 0.01050 0.00294 -0.0254 0.3781 0.1488
1.750 0.3679 0.01054 0.00299 -0.0247 0.3670 0.1677
2.250 0.4162 0.01066 0.00310 -0.0231 0.3450 0.1911
2.500 0.4404 0.01072 0.00317 -0.0223 0.3377 0.2039
2.750 0.4654 0.01075 0.00323 -0.0217 0.3307 0.2222
3.000 0.4907 0.01077 0.00331 -0.0213 0.3223 0.2534
3.250 0.5375 0.00980 0.00358 -0.0264 0.3106 0.6918
3.750 0.7274 0.01170 0.00605 -0.0567 0.2840 0.9710
4.000 0.7463 0.01195 0.00629 -0.0546 0.2782 0.9737
4.250 0.8005 0.01221 0.00645 -0.0607 0.2651 0.9758
4.500 0.8388 0.01239 0.00660 -0.0631 0.2569 0.9779
4.750 0.8635 0.01257 0.00672 -0.0626 0.2470 0.9788
5.000 0.8901 0.01314 0.00719 -0.0624 0.2299 0.9840
5.250 0.9195 0.01324 0.00724 -0.0630 0.2194 0.9844
5.500 0.9584 0.01339 0.00728 -0.0657 0.2011 0.9858
5.750 0.9853 0.01369 0.00745 -0.0658 0.1802 0.9868
6.000 1.0130 0.01386 0.00759 -0.0660 0.1736 0.9878
6.250 1.0465 0.01406 0.00775 -0.0675 0.1660 0.9904
6.500 1.0572 0.01426 0.00792 -0.0639 0.1614 0.9889
6.750 1.0874 0.01450 0.00815 -0.0647 0.1554 0.9914
7.000 1.1069 0.01470 0.00834 -0.0631 0.1521 0.9917
7.250 1.1252 0.01495 0.00857 -0.0613 0.1463 0.9921
7.500 1.1433 0.01522 0.00883 -0.0594 0.1415 0.9924
8.000 1.1854 0.01573 0.00933 -0.0570 0.1332 0.9939
8.250 1.2032 0.01601 0.00958 -0.0552 0.1271 0.9940
8.500 1.2218 0.01623 0.00981 -0.0535 0.1224 0.9941
8.750 1.2380 0.01659 0.01011 -0.0514 0.1132 0.9941
9.000 1.2533 0.01696 0.01044 -0.0492 0.1031 0.9942
9.250 1.2662 0.01746 0.01085 -0.0466 0.0892 0.9943
9.500 1.2791 0.01797 0.01130 -0.0440 0.0782 0.9944
9.750 1.2915 0.01850 0.01179 -0.0414 0.0691 0.9945
10.000 1.3061 0.01889 0.01218 -0.0392 0.0661 0.9946
10.250 1.3192 0.01936 0.01265 -0.0367 0.0624 0.9947
10.750 1.3483 0.02016 0.01350 -0.0324 0.0592 0.9948
11.000 1.3622 0.02062 0.01397 -0.0302 0.0572 0.9950
11.250 1.3787 0.02106 0.01444 -0.0287 0.0563 0.9953
11.500 1.3909 0.02160 0.01500 -0.0263 0.0546 0.9954
11.750 1.4013 0.02219 0.01561 -0.0236 0.0530 0.9954
12.000 1.4133 0.02271 0.01617 -0.0212 0.0526 0.9954
12.250 1.4250 0.02323 0.01673 -0.0188 0.0517 0.9953
12.500 1.4359 0.02381 0.01736 -0.0163 0.0511 0.9953
12.750 1.4458 0.02444 0.01803 -0.0138 0.0500 0.9952
13.000 1.4555 0.02510 0.01874 -0.0113 0.0498 0.9952
13.250 1.4642 0.02582 0.01951 -0.0087 0.0493 0.9951
13.500 1.4709 0.02667 0.02039 -0.0060 0.0481 0.9950
13.750 1.4775 0.02756 0.02131 -0.0033 0.0471 0.9949
14.000 1.4839 0.02847 0.02227 -0.0007 0.0467 0.9948
14.250 1.4892 0.02945 0.02331 0.0019 0.0461 0.9947
14.500 1.4941 0.03051 0.02442 0.0045 0.0452 0.9946
14.750 1.5001 0.03154 0.02551 0.0069 0.0450 0.9945
15.000 1.5059 0.03262 0.02665 0.0090 0.0443 0.9944
15.250 1.5111 0.03380 0.02789 0.0112 0.0435 0.9943
15.500 1.5155 0.03511 0.02925 0.0132 0.0423 0.9942
15.750 1.5203 0.03662 0.03080 0.0146 0.0411 0.9943
16.000 1.5273 0.03808 0.03234 0.0157 0.0412 0.9945
16.250 1.5270 0.03997 0.03426 0.0173 0.0395 0.9944
16.500 1.5287 0.04174 0.03611 0.0189 0.0394 0.9944
16.750 1.5292 0.04368 0.03812 0.0203 0.0380 0.9943
17.000 1.5295 0.04574 0.04024 0.0215 0.0374 0.9942
17.250 1.5283 0.04798 0.04255 0.0226 0.0359 0.9942
17.500 1.5264 0.05034 0.04498 0.0235 0.0356 0.9941
17.750 1.5207 0.05318 0.04787 0.0244 0.0338 0.9941
18.000 1.5164 0.05592 0.05069 0.0251 0.0327 0.9940
18.250 1.5089 0.05909 0.05392 0.0256 0.0306 0.9940
18.500 1.4932 0.06327 0.05813 0.0259 0.0251 0.9939
18.750 1.4670 0.06882 0.06371 0.0258 0.0198 0.9938
19.000 1.4369 0.07510 0.07007 0.0252 0.0164 0.9938
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