SG6041 (sg6041-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6041 (sg6041-il) Reynolds number: 500,000 Max Cl/Cd: 91.46 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6041-il-500000.txt Download as CSV file: xf-sg6041-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SG6041
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4465 0.08502 0.08275 -0.0394 1.0000 0.0192
-9.000 -0.4501 0.08182 0.07960 -0.0399 1.0000 0.0195
-8.750 -0.4592 0.07804 0.07586 -0.0408 1.0000 0.0195
-8.500 -0.4749 0.07445 0.07233 -0.0411 1.0000 0.0196
-8.250 -0.5243 0.07056 0.06850 -0.0396 1.0000 0.0191
-8.000 -0.5211 0.06510 0.06297 -0.0448 0.9969 0.0193
-7.750 -0.5072 0.05930 0.05704 -0.0511 0.9930 0.0197
-7.500 -0.4926 0.05411 0.05170 -0.0556 0.9883 0.0204
-7.250 -0.4738 0.04817 0.04551 -0.0602 0.9850 0.0215
-7.000 -0.4554 0.04265 0.03933 -0.0618 0.9788 0.0234
-6.750 -0.4581 0.02616 0.02154 -0.0618 0.9730 0.0140
-6.500 -0.4325 0.02180 0.01677 -0.0629 0.9715 0.0134
-6.250 -0.4127 0.01976 0.01436 -0.0615 0.9658 0.0136
-6.000 -0.3830 0.01829 0.01256 -0.0620 0.9632 0.0140
-5.750 -0.3525 0.01628 0.01032 -0.0629 0.9614 0.0142
-5.500 -0.3200 0.01491 0.00887 -0.0642 0.9600 0.0149
-5.250 -0.2848 0.01438 0.00834 -0.0660 0.9589 0.0164
-5.000 -0.2509 0.01348 0.00734 -0.0673 0.9578 0.0172
-4.750 -0.2283 0.01293 0.00672 -0.0661 0.9521 0.0181
-4.500 -0.2003 0.01192 0.00568 -0.0664 0.9487 0.0199
-4.250 -0.1683 0.01141 0.00514 -0.0672 0.9463 0.0223
-4.000 -0.1361 0.01083 0.00455 -0.0682 0.9442 0.0277
-3.750 -0.1104 0.01045 0.00419 -0.0677 0.9393 0.0381
-3.500 -0.0837 0.00999 0.00381 -0.0674 0.9346 0.0579
-3.250 -0.0536 0.00963 0.00351 -0.0679 0.9313 0.0798
-3.000 -0.0242 0.00923 0.00324 -0.0683 0.9280 0.1155
-2.750 -0.0025 0.00871 0.00304 -0.0672 0.9212 0.1975
-2.500 0.0204 0.00771 0.00276 -0.0667 0.9163 0.3990
-2.250 0.0388 0.00687 0.00267 -0.0650 0.9100 0.6151
-2.000 0.0638 0.00667 0.00264 -0.0641 0.9039 0.6875
-1.750 0.0921 0.00656 0.00257 -0.0638 0.8993 0.7239
-1.500 0.1167 0.00652 0.00255 -0.0628 0.8919 0.7495
-1.250 0.1443 0.00645 0.00247 -0.0624 0.8860 0.7698
-1.000 0.1701 0.00641 0.00244 -0.0617 0.8787 0.7875
-0.750 0.1971 0.00637 0.00238 -0.0612 0.8717 0.8038
-0.500 0.2226 0.00634 0.00236 -0.0604 0.8637 0.8219
-0.250 0.2478 0.00630 0.00234 -0.0593 0.8559 0.8433
0.000 0.2722 0.00627 0.00235 -0.0582 0.8467 0.8603
0.250 0.2981 0.00624 0.00230 -0.0574 0.8383 0.8737
0.500 0.3233 0.00620 0.00226 -0.0565 0.8276 0.8852
0.750 0.3488 0.00616 0.00222 -0.0558 0.8161 0.8951
1.000 0.3747 0.00613 0.00217 -0.0551 0.8047 0.9041
1.250 0.4005 0.00611 0.00213 -0.0544 0.7919 0.9142
1.500 0.4261 0.00609 0.00210 -0.0537 0.7773 0.9246
1.750 0.4524 0.00609 0.00209 -0.0531 0.7599 0.9350
2.000 0.4799 0.00613 0.00206 -0.0528 0.7393 0.9460
2.250 0.5092 0.00620 0.00207 -0.0530 0.7166 0.9572
2.500 0.5426 0.00633 0.00210 -0.0541 0.6889 0.9654
2.750 0.5760 0.00650 0.00216 -0.0553 0.6557 0.9741
3.000 0.6095 0.00674 0.00223 -0.0566 0.6177 0.9825
3.250 0.6448 0.00705 0.00233 -0.0584 0.5679 0.9887
3.500 0.6789 0.00744 0.00248 -0.0601 0.5122 0.9963
3.750 0.7037 0.00781 0.00263 -0.0599 0.4619 1.0000
4.000 0.7182 0.00816 0.00278 -0.0574 0.4197 1.0000
4.250 0.7354 0.00853 0.00296 -0.0554 0.3802 1.0000
4.500 0.7541 0.00891 0.00317 -0.0538 0.3402 1.0000
4.750 0.7738 0.00932 0.00340 -0.0523 0.3020 1.0000
5.000 0.7944 0.00972 0.00364 -0.0511 0.2681 1.0000
5.250 0.8156 0.01011 0.00389 -0.0500 0.2387 1.0000
5.500 0.8373 0.01049 0.00417 -0.0489 0.2127 1.0000
5.750 0.8589 0.01090 0.00446 -0.0479 0.1888 1.0000
6.000 0.8809 0.01129 0.00476 -0.0470 0.1677 1.0000
6.250 0.9028 0.01169 0.00508 -0.0460 0.1501 1.0000
6.500 0.9246 0.01211 0.00542 -0.0451 0.1339 1.0000
6.750 0.9466 0.01252 0.00577 -0.0441 0.1197 1.0000
7.000 0.9686 0.01292 0.00612 -0.0432 0.1077 1.0000
7.250 0.9908 0.01329 0.00650 -0.0424 0.0978 1.0000
7.500 1.0125 0.01371 0.00691 -0.0414 0.0897 1.0000
7.750 1.0335 0.01419 0.00735 -0.0403 0.0819 1.0000
8.000 1.0553 0.01457 0.00778 -0.0394 0.0762 1.0000
8.250 1.0756 0.01508 0.00826 -0.0383 0.0696 1.0000
8.500 1.0967 0.01550 0.00873 -0.0372 0.0651 1.0000
8.750 1.1172 0.01596 0.00920 -0.0361 0.0602 1.0000
9.000 1.1352 0.01659 0.00985 -0.0346 0.0553 1.0000
9.250 1.1560 0.01699 0.01031 -0.0336 0.0512 1.0000
9.500 1.1699 0.01787 0.01117 -0.0315 0.0459 1.0000
9.750 1.1896 0.01824 0.01163 -0.0302 0.0434 1.0000
10.000 1.2066 0.01876 0.01218 -0.0286 0.0402 1.0000
10.250 1.2155 0.01979 0.01323 -0.0257 0.0369 1.0000
10.500 1.2325 0.02032 0.01385 -0.0241 0.0352 1.0000
10.750 1.2482 0.02091 0.01452 -0.0224 0.0332 1.0000
11.000 1.2623 0.02161 0.01527 -0.0206 0.0314 1.0000
11.250 1.2711 0.02268 0.01638 -0.0181 0.0296 1.0000
11.500 1.2790 0.02386 0.01766 -0.0156 0.0283 1.0000
11.750 1.2923 0.02465 0.01856 -0.0138 0.0274 1.0000
12.000 1.3044 0.02551 0.01951 -0.0121 0.0261 1.0000
12.250 1.3151 0.02647 0.02056 -0.0103 0.0251 1.0000
12.500 1.3251 0.02747 0.02162 -0.0085 0.0239 1.0000
12.750 1.3271 0.02918 0.02341 -0.0061 0.0229 1.0000
13.000 1.3272 0.03120 0.02556 -0.0037 0.0221 1.0000
13.250 1.3361 0.03241 0.02689 -0.0023 0.0215 1.0000
13.500 1.3427 0.03386 0.02848 -0.0008 0.0208 1.0000
13.750 1.3486 0.03539 0.03012 0.0005 0.0200 1.0000
14.000 1.3526 0.03713 0.03197 0.0017 0.0193 1.0000
14.250 1.3571 0.03886 0.03378 0.0026 0.0186 1.0000
14.500 1.3570 0.04111 0.03610 0.0035 0.0179 1.0000
14.750 1.3500 0.04431 0.03942 0.0043 0.0174 1.0000
15.000 1.3412 0.04790 0.04318 0.0048 0.0168 1.0000
15.250 1.3402 0.05076 0.04621 0.0047 0.0165 1.0000
15.500 1.3401 0.05365 0.04924 0.0042 0.0160 1.0000
15.750 1.3356 0.05727 0.05301 0.0033 0.0156 1.0000
16.000 1.3311 0.06113 0.05701 0.0021 0.0152 1.0000
16.250 1.3235 0.06565 0.06166 0.0004 0.0149 1.0000
16.500 1.3143 0.07067 0.06683 -0.0018 0.0146 1.0000
16.750 1.3047 0.07599 0.07229 -0.0044 0.0144 1.0000
17.000 1.2934 0.08185 0.07827 -0.0074 0.0141 1.0000
17.250 1.2810 0.08814 0.08468 -0.0108 0.0140 1.0000
17.500 1.2667 0.09494 0.09161 -0.0146 0.0138 1.0000
17.750 1.2523 0.10200 0.09879 -0.0186 0.0137 1.0000
18.000 1.2359 0.10962 0.10654 -0.0230 0.0136 1.0000
18.250 1.2180 0.11770 0.11475 -0.0277 0.0135 1.0000
18.500 1.2001 0.12602 0.12320 -0.0326 0.0134 1.0000
18.750 1.1801 0.13508 0.13241 -0.0381 0.0134 1.0000
19.000 1.1613 0.14410 0.14156 -0.0436 0.0133 1.0000
19.250 1.1389 0.15440 0.15200 -0.0500 0.0134 1.0000
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