S2048 (s2048-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2048 (s2048-il) Reynolds number: 500,000 Max Cl/Cd: 78.13 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2048-il-500000-n5.txt Download as CSV file: xf-s2048-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5048 0.08094 0.07869 -0.0344 1.0000 0.0062
-9.250 -0.5169 0.07510 0.07290 -0.0369 1.0000 0.0064
-9.000 -0.5322 0.06988 0.06776 -0.0392 1.0000 0.0062
-8.750 -0.5519 0.06539 0.06334 -0.0409 1.0000 0.0061
-8.500 -0.5788 0.05867 0.05658 -0.0448 1.0000 0.0061
-8.250 -0.6124 0.03206 0.02887 -0.0596 0.9909 0.0063
-8.000 -0.5968 0.02545 0.02146 -0.0617 0.9867 0.0067
-7.750 -0.5729 0.02169 0.01715 -0.0632 0.9844 0.0071
-7.500 -0.5433 0.02035 0.01562 -0.0647 0.9830 0.0076
-7.250 -0.5166 0.01957 0.01473 -0.0651 0.9802 0.0080
-7.000 -0.4893 0.01858 0.01356 -0.0656 0.9772 0.0085
-6.750 -0.4601 0.01751 0.01229 -0.0664 0.9749 0.0093
-6.500 -0.4293 0.01662 0.01123 -0.0674 0.9731 0.0103
-6.250 -0.3970 0.01608 0.01056 -0.0687 0.9716 0.0112
-6.000 -0.3645 0.01552 0.00986 -0.0699 0.9703 0.0117
-5.750 -0.3391 0.01396 0.00811 -0.0698 0.9667 0.0124
-5.500 -0.3126 0.01298 0.00702 -0.0698 0.9627 0.0131
-5.250 -0.2829 0.01242 0.00641 -0.0705 0.9599 0.0142
-5.000 -0.2522 0.01188 0.00580 -0.0713 0.9574 0.0152
-4.750 -0.2240 0.01133 0.00518 -0.0714 0.9539 0.0160
-4.500 -0.1977 0.01087 0.00466 -0.0712 0.9486 0.0167
-4.250 -0.1685 0.01046 0.00417 -0.0715 0.9448 0.0174
-4.000 -0.1390 0.01010 0.00374 -0.0719 0.9413 0.0179
-3.750 -0.1130 0.00980 0.00338 -0.0715 0.9347 0.0182
-3.500 -0.0841 0.00947 0.00299 -0.0718 0.9302 0.0195
-3.250 -0.0566 0.00920 0.00267 -0.0717 0.9242 0.0211
-3.000 -0.0284 0.00897 0.00241 -0.0717 0.9181 0.0229
-2.750 -0.0002 0.00875 0.00217 -0.0717 0.9120 0.0280
-2.500 0.0273 0.00843 0.00197 -0.0717 0.9048 0.0606
-2.250 0.0551 0.00818 0.00181 -0.0717 0.8976 0.0919
-2.000 0.0826 0.00787 0.00165 -0.0717 0.8894 0.1410
-1.750 0.1090 0.00735 0.00148 -0.0717 0.8792 0.2550
-1.500 0.1353 0.00688 0.00133 -0.0716 0.8669 0.3701
-1.250 0.1610 0.00643 0.00124 -0.0713 0.8517 0.4955
-1.000 0.1865 0.00617 0.00124 -0.0708 0.8343 0.5999
-0.750 0.2126 0.00610 0.00122 -0.0702 0.8164 0.6470
-0.500 0.2387 0.00605 0.00123 -0.0697 0.7995 0.6868
-0.250 0.2652 0.00604 0.00123 -0.0692 0.7843 0.7117
0.000 0.2920 0.00606 0.00123 -0.0689 0.7701 0.7292
0.250 0.3189 0.00608 0.00123 -0.0686 0.7563 0.7432
0.500 0.3457 0.00611 0.00124 -0.0683 0.7414 0.7558
0.750 0.3723 0.00615 0.00126 -0.0679 0.7251 0.7684
1.000 0.3987 0.00620 0.00130 -0.0675 0.7075 0.7816
1.250 0.4249 0.00626 0.00133 -0.0671 0.6868 0.7956
1.500 0.4504 0.00634 0.00138 -0.0665 0.6613 0.8107
1.750 0.4755 0.00645 0.00143 -0.0658 0.6328 0.8274
2.000 0.4994 0.00660 0.00152 -0.0649 0.5956 0.8461
2.250 0.5222 0.00681 0.00162 -0.0637 0.5503 0.8684
2.500 0.5440 0.00704 0.00174 -0.0624 0.5037 0.8962
2.750 0.5671 0.00731 0.00188 -0.0613 0.4546 0.9329
3.000 0.6000 0.00768 0.00206 -0.0627 0.3990 0.9810
3.250 0.6254 0.00815 0.00226 -0.0625 0.3399 1.0000
3.500 0.6495 0.00856 0.00246 -0.0620 0.2951 1.0000
4.000 0.6998 0.00918 0.00288 -0.0612 0.2409 1.0000
4.250 0.7249 0.00949 0.00309 -0.0608 0.2162 1.0000
4.500 0.7499 0.00982 0.00332 -0.0604 0.1933 1.0000
4.750 0.7749 0.01015 0.00356 -0.0600 0.1694 1.0000
5.000 0.7997 0.01049 0.00382 -0.0596 0.1458 1.0000
5.250 0.8234 0.01096 0.00414 -0.0591 0.1128 1.0000
5.500 0.8470 0.01145 0.00453 -0.0585 0.0853 1.0000
5.750 0.8711 0.01189 0.00490 -0.0579 0.0679 1.0000
6.000 0.8949 0.01235 0.00529 -0.0574 0.0530 1.0000
6.250 0.9188 0.01280 0.00569 -0.0568 0.0416 1.0000
6.500 0.9430 0.01320 0.00609 -0.0563 0.0340 1.0000
6.750 0.9667 0.01366 0.00653 -0.0557 0.0278 1.0000
7.000 0.9909 0.01404 0.00695 -0.0552 0.0240 1.0000
7.250 1.0142 0.01454 0.00746 -0.0545 0.0186 1.0000
7.500 1.0372 0.01504 0.00796 -0.0539 0.0136 1.0000
7.750 1.0600 0.01557 0.00852 -0.0532 0.0101 1.0000
8.000 1.0818 0.01621 0.00919 -0.0523 0.0075 1.0000
8.250 1.1038 0.01682 0.00987 -0.0514 0.0065 1.0000
8.500 1.1250 0.01751 0.01062 -0.0505 0.0056 1.0000
8.750 1.1449 0.01834 0.01156 -0.0493 0.0050 1.0000
9.000 1.1629 0.01938 0.01276 -0.0478 0.0046 1.0000
9.250 1.1819 0.02021 0.01372 -0.0466 0.0044 1.0000
9.500 1.2001 0.02111 0.01474 -0.0453 0.0042 1.0000
9.750 1.2179 0.02199 0.01574 -0.0439 0.0039 1.0000
10.000 1.2354 0.02286 0.01671 -0.0426 0.0037 1.0000
10.250 1.2512 0.02383 0.01781 -0.0410 0.0034 1.0000
10.500 1.2657 0.02488 0.01898 -0.0393 0.0033 1.0000
10.750 1.2778 0.02601 0.02026 -0.0372 0.0032 1.0000
11.000 1.2868 0.02720 0.02158 -0.0347 0.0031 1.0000
11.250 1.2939 0.02846 0.02301 -0.0321 0.0030 1.0000
11.500 1.2993 0.02985 0.02455 -0.0294 0.0029 1.0000
11.750 1.3024 0.03142 0.02628 -0.0267 0.0028 1.0000
12.000 1.3028 0.03326 0.02829 -0.0240 0.0027 1.0000
12.250 1.2979 0.03563 0.03086 -0.0212 0.0026 1.0000
12.500 1.2933 0.03810 0.03352 -0.0190 0.0026 1.0000
12.750 1.2882 0.04076 0.03637 -0.0172 0.0026 1.0000
13.000 1.2796 0.04397 0.03978 -0.0160 0.0026 1.0000
13.250 1.2550 0.04940 0.04550 -0.0156 0.0025 1.0000
13.500 1.2439 0.05371 0.04999 -0.0162 0.0025 1.0000
13.750 1.2290 0.05903 0.05551 -0.0179 0.0025 1.0000
14.000 1.2171 0.06455 0.06120 -0.0205 0.0025 1.0000
14.250 1.2006 0.07157 0.06841 -0.0245 0.0025 1.0000
14.500 1.1805 0.08022 0.07725 -0.0299 0.0025 1.0000
14.750 1.1661 0.08830 0.08548 -0.0350 0.0025 1.0000
15.000 1.1475 0.09764 0.09496 -0.0408 0.0025 1.0000
15.250 1.1243 0.10825 0.10571 -0.0470 0.0025 1.0000
15.500 1.1118 0.11637 0.11392 -0.0516 0.0026 1.0000
15.750 1.0925 0.12637 0.12403 -0.0573 0.0026 1.0000
16.000 1.0716 0.13715 0.13492 -0.0632 0.0028 1.0000
16.250 1.0385 0.15222 0.15012 -0.0714 0.0028 1.0000
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Polar data table (+)
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