S2048 (s2048-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2048 (s2048-il) Reynolds number: 500,000 Max Cl/Cd: 100.66 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2048-il-500000.txt Download as CSV file: xf-s2048-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S2048
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4661 0.08222 0.08000 -0.0336 1.0000 0.0184
-8.500 -0.4723 0.07841 0.07623 -0.0347 1.0000 0.0186
-8.250 -0.4835 0.07459 0.07246 -0.0356 1.0000 0.0191
-8.000 -0.5020 0.07153 0.06947 -0.0351 1.0000 0.0188
-7.750 -0.5190 0.06652 0.06447 -0.0384 1.0000 0.0187
-7.500 -0.5310 0.06201 0.05993 -0.0394 1.0000 0.0185
-7.250 -0.5391 0.05772 0.05557 -0.0395 1.0000 0.0189
-7.000 -0.5335 0.05199 0.04964 -0.0420 0.9989 0.0200
-6.750 -0.5006 0.04699 0.04423 -0.0470 0.9957 0.0213
-6.500 -0.4763 0.04172 0.03857 -0.0508 0.9925 0.0214
-6.250 -0.4629 0.03253 0.02900 -0.0552 0.9880 0.0235
-6.000 -0.4326 0.03019 0.02647 -0.0575 0.9856 0.0250
-5.750 -0.4033 0.02094 0.01611 -0.0584 0.9836 0.0178
-5.500 -0.3743 0.01887 0.01372 -0.0589 0.9804 0.0188
-5.250 -0.3435 0.01746 0.01208 -0.0597 0.9772 0.0199
-5.000 -0.3108 0.01586 0.01023 -0.0606 0.9749 0.0206
-4.750 -0.2765 0.01481 0.00901 -0.0620 0.9730 0.0211
-4.500 -0.2428 0.01329 0.00733 -0.0634 0.9716 0.0221
-4.250 -0.2082 0.01204 0.00601 -0.0651 0.9703 0.0242
-4.000 -0.1812 0.01142 0.00534 -0.0650 0.9650 0.0255
-3.750 -0.1478 0.01089 0.00475 -0.0662 0.9621 0.0273
-3.500 -0.1120 0.01043 0.00422 -0.0679 0.9601 0.0292
-3.250 -0.0751 0.00996 0.00370 -0.0699 0.9585 0.0337
-3.000 -0.0389 0.00940 0.00327 -0.0717 0.9570 0.0658
-2.750 -0.0124 0.00882 0.00300 -0.0717 0.9511 0.1488
-2.500 0.0179 0.00802 0.00274 -0.0728 0.9471 0.2995
-2.250 0.0483 0.00715 0.00256 -0.0738 0.9441 0.5020
-2.000 0.0756 0.00682 0.00252 -0.0736 0.9384 0.5988
-1.750 0.1046 0.00663 0.00240 -0.0736 0.9325 0.6402
-1.500 0.1341 0.00644 0.00228 -0.0736 0.9267 0.6782
-1.250 0.1610 0.00627 0.00216 -0.0730 0.9177 0.7062
-1.000 0.1877 0.00613 0.00203 -0.0724 0.9074 0.7285
-0.750 0.2145 0.00599 0.00193 -0.0718 0.8969 0.7533
-0.500 0.2412 0.00588 0.00185 -0.0711 0.8866 0.7793
-0.250 0.2674 0.00582 0.00181 -0.0705 0.8753 0.8007
0.000 0.2937 0.00576 0.00177 -0.0699 0.8643 0.8179
0.250 0.3201 0.00571 0.00174 -0.0693 0.8536 0.8343
0.500 0.3464 0.00568 0.00172 -0.0688 0.8428 0.8512
0.750 0.3723 0.00566 0.00170 -0.0681 0.8314 0.8699
1.000 0.3971 0.00562 0.00171 -0.0672 0.8192 0.8908
1.250 0.4215 0.00560 0.00171 -0.0661 0.8061 0.9166
1.500 0.4493 0.00558 0.00171 -0.0658 0.7930 0.9469
1.750 0.4865 0.00559 0.00170 -0.0677 0.7778 0.9758
2.000 0.5242 0.00563 0.00171 -0.0698 0.7613 1.0000
2.250 0.5497 0.00572 0.00174 -0.0694 0.7425 1.0000
2.500 0.5750 0.00584 0.00179 -0.0688 0.7204 1.0000
2.750 0.6003 0.00598 0.00184 -0.0682 0.6937 1.0000
3.000 0.6241 0.00620 0.00192 -0.0673 0.6512 1.0000
3.250 0.6456 0.00657 0.00201 -0.0660 0.5840 1.0000
3.500 0.6661 0.00710 0.00219 -0.0646 0.5061 1.0000
3.750 0.6875 0.00764 0.00242 -0.0635 0.4369 1.0000
4.000 0.7099 0.00815 0.00268 -0.0626 0.3782 1.0000
4.250 0.7331 0.00861 0.00293 -0.0619 0.3303 1.0000
4.500 0.7569 0.00903 0.00319 -0.0613 0.2916 1.0000
4.750 0.7812 0.00941 0.00345 -0.0608 0.2607 1.0000
5.000 0.8055 0.00979 0.00372 -0.0602 0.2315 1.0000
5.250 0.8300 0.01016 0.00402 -0.0598 0.2055 1.0000
5.500 0.8540 0.01056 0.00432 -0.0592 0.1765 1.0000
5.750 0.8772 0.01108 0.00466 -0.0586 0.1371 1.0000
6.000 0.8986 0.01181 0.00514 -0.0577 0.0922 1.0000
6.250 0.9206 0.01249 0.00567 -0.0568 0.0653 1.0000
6.500 0.9435 0.01304 0.00619 -0.0561 0.0507 1.0000
6.750 0.9664 0.01361 0.00674 -0.0553 0.0411 1.0000
7.000 0.9890 0.01419 0.00731 -0.0545 0.0335 1.0000
7.250 1.0124 0.01469 0.00786 -0.0538 0.0279 1.0000
7.500 1.0336 0.01545 0.00863 -0.0528 0.0209 1.0000
7.750 1.0526 0.01648 0.00968 -0.0514 0.0152 1.0000
8.000 1.0748 0.01708 0.01038 -0.0505 0.0132 1.0000
8.250 1.0954 0.01785 0.01122 -0.0494 0.0118 1.0000
8.500 1.1095 0.01941 0.01289 -0.0473 0.0105 1.0000
8.750 1.1254 0.02079 0.01442 -0.0454 0.0099 1.0000
9.000 1.1431 0.02193 0.01571 -0.0439 0.0095 1.0000
9.250 1.1596 0.02328 0.01721 -0.0422 0.0091 1.0000
9.500 1.1748 0.02488 0.01898 -0.0404 0.0088 1.0000
9.750 1.1893 0.02658 0.02087 -0.0386 0.0085 1.0000
10.000 1.2032 0.02815 0.02263 -0.0368 0.0082 1.0000
10.250 1.2164 0.02950 0.02413 -0.0350 0.0079 1.0000
10.500 1.2281 0.03065 0.02539 -0.0331 0.0075 1.0000
10.750 1.2345 0.03210 0.02695 -0.0305 0.0072 1.0000
11.000 1.2357 0.03435 0.02942 -0.0274 0.0071 1.0000
11.250 1.2337 0.03677 0.03207 -0.0241 0.0071 1.0000
11.500 1.2283 0.03939 0.03493 -0.0210 0.0070 1.0000
11.750 1.2200 0.04228 0.03805 -0.0182 0.0070 1.0000
12.000 1.2096 0.04544 0.04144 -0.0159 0.0070 1.0000
12.250 1.1962 0.04906 0.04530 -0.0143 0.0070 1.0000
12.500 1.1816 0.05311 0.04956 -0.0137 0.0070 1.0000
12.750 1.1655 0.05773 0.05438 -0.0141 0.0069 1.0000
13.000 1.1475 0.06318 0.06004 -0.0157 0.0069 1.0000
13.250 1.1334 0.06870 0.06574 -0.0183 0.0070 1.0000
13.500 1.1151 0.07580 0.07304 -0.0225 0.0071 1.0000
13.750 1.0833 0.08721 0.08474 -0.0302 0.0073 1.0000
14.000 1.0492 0.10101 0.09877 -0.0397 0.0075 1.0000
14.250 0.9054 0.15418 0.15213 -0.0674 0.0114 1.0000
14.500 0.9098 0.15776 0.15571 -0.0694 0.0111 1.0000
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Polar data table (+)
Polar graphs
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