GOE 459 AIRFOIL (goe459-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 459 AIRFOIL (goe459-il) Reynolds number: 200,000 Max Cl/Cd: 49.27 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe459-il-200000.txt Download as CSV file: xf-goe459-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 459 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
------ -------- --------- --------- -------- -------- --------
-15.500 -0.9256 0.08235 0.07776 -0.0454 1.0000 0.0339
-15.250 -0.9534 0.07480 0.07002 -0.0495 1.0000 0.0337
-15.000 -0.9845 0.06778 0.06273 -0.0534 1.0000 0.0340
-14.750 -1.0061 0.06240 0.05712 -0.0553 1.0000 0.0340
-14.500 -1.0270 0.05768 0.05216 -0.0563 1.0000 0.0341
-14.250 -1.0383 0.05376 0.04810 -0.0562 1.0000 0.0345
-14.000 -1.0301 0.05245 0.04688 -0.0559 1.0000 0.0356
-13.750 -1.0339 0.05018 0.04453 -0.0553 1.0000 0.0364
-13.500 -1.0390 0.04793 0.04214 -0.0542 1.0000 0.0373
-13.250 -1.0464 0.04544 0.03947 -0.0526 1.0000 0.0381
-13.000 -1.0546 0.04311 0.03692 -0.0503 1.0000 0.0391
-12.750 -1.0651 0.04117 0.03468 -0.0471 1.0000 0.0403
-12.500 -1.0734 0.03919 0.03242 -0.0435 1.0000 0.0412
-12.250 -1.0624 0.03779 0.03115 -0.0421 1.0000 0.0433
-12.000 -1.0607 0.03689 0.03017 -0.0389 1.0000 0.0450
-11.750 -1.0624 0.03581 0.02893 -0.0349 1.0000 0.0471
-11.500 -1.0674 0.03502 0.02789 -0.0300 1.0000 0.0489
-11.250 -1.0563 0.03296 0.02585 -0.0283 1.0000 0.0522
-11.000 -1.0487 0.03211 0.02495 -0.0255 1.0000 0.0552
-10.750 -1.0447 0.03143 0.02404 -0.0217 1.0000 0.0584
-10.500 -1.0316 0.02957 0.02213 -0.0200 1.0000 0.0620
-10.250 -1.0199 0.02889 0.02143 -0.0177 1.0000 0.0654
-10.000 -1.0089 0.02821 0.02058 -0.0150 1.0000 0.0685
-9.750 -0.9953 0.02700 0.01920 -0.0128 1.0000 0.0713
-9.500 -0.9781 0.02591 0.01816 -0.0114 1.0000 0.0746
-9.250 -0.9630 0.02522 0.01742 -0.0094 1.0000 0.0775
-9.000 -0.9482 0.02461 0.01667 -0.0071 1.0000 0.0804
-8.750 -0.9319 0.02375 0.01570 -0.0053 1.0000 0.0832
-8.500 -0.9154 0.02286 0.01489 -0.0036 1.0000 0.0870
-8.250 -0.8994 0.02230 0.01429 -0.0016 1.0000 0.0903
-8.000 -0.8822 0.02166 0.01356 0.0004 1.0000 0.0927
-7.750 -0.8649 0.02107 0.01285 0.0023 1.0000 0.0945
-7.500 -0.8487 0.02008 0.01193 0.0043 1.0000 0.0971
-7.250 -0.8337 0.01942 0.01129 0.0066 1.0000 0.0995
-7.000 -0.8189 0.01887 0.01074 0.0089 1.0000 0.1021
-6.750 -0.8042 0.01837 0.01019 0.0113 1.0000 0.1051
-6.500 -0.7898 0.01788 0.00966 0.0138 1.0000 0.1084
-6.250 -0.7778 0.01730 0.00915 0.0166 1.0000 0.1130
-6.000 -0.7637 0.01690 0.00874 0.0191 1.0000 0.1194
-5.750 -0.7515 0.01638 0.00831 0.0219 1.0000 0.1284
-5.500 -0.7392 0.01587 0.00789 0.0246 1.0000 0.1438
-5.250 -0.7287 0.01523 0.00745 0.0276 1.0000 0.1748
-5.000 -0.7176 0.01469 0.00714 0.0304 1.0000 0.2155
-4.750 -0.7046 0.01432 0.00693 0.0328 1.0000 0.2529
-4.500 -0.6909 0.01402 0.00674 0.0352 1.0000 0.2845
-4.250 -0.6553 0.01372 0.00664 0.0330 0.9949 0.3288
-4.000 -0.6212 0.01334 0.00654 0.0312 0.9887 0.3816
-3.750 -0.5845 0.01308 0.00656 0.0290 0.9830 0.4465
-3.500 -0.5533 0.01281 0.00649 0.0281 0.9753 0.5011
-3.250 -0.5153 0.01264 0.00650 0.0259 0.9704 0.5499
-3.000 -0.4859 0.01242 0.00643 0.0257 0.9617 0.5912
-2.750 -0.4466 0.01227 0.00644 0.0235 0.9569 0.6322
-2.500 -0.4175 0.01212 0.00637 0.0234 0.9479 0.6631
-2.250 -0.3780 0.01198 0.00633 0.0212 0.9432 0.6951
-2.000 -0.3477 0.01185 0.00628 0.0210 0.9345 0.7233
-1.750 -0.3079 0.01169 0.00619 0.0190 0.9294 0.7512
-1.500 -0.2700 0.01157 0.00616 0.0173 0.9236 0.7741
-1.250 -0.2323 0.01144 0.00607 0.0157 0.9167 0.7948
-1.000 -0.1835 0.01125 0.00594 0.0120 0.9131 0.8167
-0.750 -0.1413 0.01116 0.00590 0.0098 0.9049 0.8368
-0.500 -0.0913 0.01102 0.00579 0.0060 0.8984 0.8539
-0.250 -0.0471 0.01094 0.00572 0.0034 0.8883 0.8679
0.000 0.0000 0.01084 0.00560 0.0000 0.8799 0.8799
0.250 0.0473 0.01094 0.00572 -0.0034 0.8678 0.8883
0.500 0.0913 0.01102 0.00579 -0.0060 0.8540 0.8984
0.750 0.1414 0.01116 0.00590 -0.0098 0.8368 0.9050
1.000 0.1839 0.01126 0.00594 -0.0121 0.8166 0.9132
1.250 0.2325 0.01144 0.00607 -0.0158 0.7951 0.9167
1.500 0.2701 0.01157 0.00616 -0.0173 0.7742 0.9236
1.750 0.3079 0.01169 0.00619 -0.0190 0.7512 0.9294
2.000 0.3478 0.01185 0.00628 -0.0211 0.7237 0.9345
2.250 0.3780 0.01198 0.00632 -0.0212 0.6942 0.9432
2.500 0.4175 0.01212 0.00637 -0.0233 0.6621 0.9480
2.750 0.4466 0.01227 0.00643 -0.0235 0.6318 0.9569
3.000 0.4857 0.01242 0.00642 -0.0256 0.5898 0.9617
3.250 0.5152 0.01263 0.00650 -0.0259 0.5496 0.9704
3.500 0.5534 0.01281 0.00649 -0.0281 0.5009 0.9754
3.750 0.5846 0.01308 0.00655 -0.0290 0.4463 0.9831
4.000 0.6211 0.01334 0.00654 -0.0312 0.3817 0.9887
4.250 0.6554 0.01371 0.00664 -0.0330 0.3289 0.9949
4.500 0.6908 0.01402 0.00674 -0.0352 0.2848 1.0000
4.750 0.7045 0.01432 0.00693 -0.0328 0.2524 1.0000
5.000 0.7175 0.01468 0.00713 -0.0304 0.2153 1.0000
5.250 0.7287 0.01522 0.00744 -0.0276 0.1759 1.0000
5.500 0.7392 0.01587 0.00788 -0.0246 0.1441 1.0000
5.750 0.7513 0.01639 0.00832 -0.0219 0.1280 1.0000
6.000 0.7637 0.01690 0.00874 -0.0191 0.1197 1.0000
6.250 0.7778 0.01729 0.00915 -0.0166 0.1131 1.0000
6.500 0.7897 0.01789 0.00966 -0.0138 0.1084 1.0000
6.750 0.8041 0.01837 0.01019 -0.0113 0.1053 1.0000
7.000 0.8189 0.01887 0.01073 -0.0089 0.1022 1.0000
7.250 0.8338 0.01942 0.01129 -0.0066 0.0997 1.0000
7.500 0.8487 0.02007 0.01192 -0.0043 0.0972 1.0000
7.750 0.8649 0.02107 0.01285 -0.0023 0.0945 1.0000
8.000 0.8822 0.02165 0.01355 -0.0004 0.0927 1.0000
8.250 0.8994 0.02229 0.01428 0.0016 0.0904 1.0000
8.500 0.9154 0.02286 0.01489 0.0036 0.0870 1.0000
8.750 0.9319 0.02372 0.01567 0.0053 0.0833 1.0000
9.000 0.9481 0.02459 0.01665 0.0072 0.0803 1.0000
9.250 0.9631 0.02522 0.01742 0.0093 0.0776 1.0000
9.500 0.9780 0.02588 0.01814 0.0114 0.0745 1.0000
9.750 0.9954 0.02704 0.01923 0.0128 0.0712 1.0000
10.000 1.0086 0.02818 0.02055 0.0150 0.0684 1.0000
10.250 1.0199 0.02889 0.02143 0.0177 0.0653 1.0000
10.500 1.0319 0.02963 0.02220 0.0200 0.0620 1.0000
10.750 1.0443 0.03140 0.02401 0.0218 0.0583 1.0000
11.000 1.0489 0.03215 0.02499 0.0254 0.0552 1.0000
11.250 1.0566 0.03297 0.02587 0.0283 0.0521 1.0000
11.500 1.0687 0.03512 0.02797 0.0297 0.0490 1.0000
11.750 1.0623 0.03583 0.02896 0.0349 0.0470 1.0000
12.000 1.0605 0.03676 0.03004 0.0390 0.0448 1.0000
12.250 1.0630 0.03768 0.03102 0.0420 0.0431 1.0000
12.500 1.0736 0.03914 0.03238 0.0435 0.0413 1.0000
12.750 1.0645 0.04109 0.03461 0.0472 0.0402 1.0000
13.000 1.0557 0.04318 0.03698 0.0502 0.0392 1.0000
13.250 1.0470 0.04555 0.03959 0.0525 0.0383 1.0000
13.500 1.0409 0.04775 0.04195 0.0541 0.0371 1.0000
13.750 1.0329 0.05046 0.04483 0.0552 0.0365 1.0000
14.000 1.0296 0.05263 0.04709 0.0557 0.0358 1.0000
14.250 1.0297 0.05476 0.04924 0.0560 0.0350 1.0000
14.500 1.0273 0.05774 0.05221 0.0561 0.0341 1.0000
14.750 1.0081 0.06235 0.05707 0.0552 0.0340 1.0000
15.000 0.9845 0.06777 0.06273 0.0530 0.0338 1.0000
15.250 0.9585 0.07434 0.06953 0.0499 0.0339 1.0000
15.500 0.9316 0.08162 0.07700 0.0458 0.0339 1.0000
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