S2048 (s2048-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2048 (s2048-il) Reynolds number: 100,000 Max Cl/Cd: 55.79 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2048-il-100000.txt Download as CSV file: xf-s2048-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4536 0.09232 0.08745 -0.0295 1.0000 0.1041
-8.250 -0.4716 0.08955 0.08481 -0.0325 1.0000 0.1074
-8.000 -0.4977 0.08645 0.08186 -0.0373 1.0000 0.1082
-7.750 -0.4925 0.08218 0.07765 -0.0348 1.0000 0.1106
-7.500 -0.4805 0.07980 0.07528 -0.0307 1.0000 0.1154
-7.250 -0.4913 0.07605 0.07159 -0.0339 1.0000 0.1196
-7.000 -0.5183 0.07160 0.06700 -0.0405 1.0000 0.1234
-6.750 -0.4992 0.06877 0.06435 -0.0349 1.0000 0.1277
-6.500 -0.5167 0.06533 0.06059 -0.0400 1.0000 0.1371
-6.250 -0.5017 0.06180 0.05732 -0.0355 1.0000 0.1412
-6.000 -0.5028 0.05827 0.05361 -0.0370 1.0000 0.1526
-5.750 -0.4930 0.05567 0.05107 -0.0348 1.0000 0.1603
-5.500 -0.4897 0.05253 0.04769 -0.0358 1.0000 0.1801
-5.250 -0.4801 0.04988 0.04510 -0.0337 1.0000 0.1956
-5.000 -0.4407 0.03823 0.03159 -0.0399 1.0000 0.0940
-4.750 -0.4181 0.03290 0.02579 -0.0394 1.0000 0.0772
-4.500 -0.3917 0.03006 0.02193 -0.0380 1.0000 0.0678
-4.250 -0.3685 0.02694 0.01847 -0.0375 1.0000 0.0667
-4.000 -0.3442 0.02484 0.01600 -0.0367 1.0000 0.0667
-3.750 -0.3203 0.02290 0.01388 -0.0362 1.0000 0.0709
-3.500 -0.2961 0.02160 0.01245 -0.0354 1.0000 0.0745
-3.250 -0.2717 0.02038 0.01109 -0.0345 1.0000 0.0777
-3.000 -0.2479 0.01920 0.00985 -0.0336 1.0000 0.0828
-2.750 -0.2249 0.01831 0.00897 -0.0327 1.0000 0.0948
-2.500 -0.2017 0.01707 0.00802 -0.0322 1.0000 0.1284
-2.250 -0.1833 0.01414 0.00759 -0.0307 1.0000 0.6186
-2.000 -0.1760 0.01403 0.00794 -0.0252 1.0000 0.7716
-1.750 -0.1699 0.01396 0.00804 -0.0196 1.0000 0.8551
-1.500 -0.1409 0.01381 0.00788 -0.0189 1.0000 0.9534
-1.250 -0.1097 0.01376 0.00758 -0.0210 1.0000 1.0000
-1.000 -0.0852 0.01392 0.00749 -0.0216 1.0000 1.0000
-0.750 -0.0611 0.01413 0.00749 -0.0221 1.0000 1.0000
-0.500 -0.0376 0.01438 0.00754 -0.0223 1.0000 1.0000
-0.250 -0.0145 0.01467 0.00767 -0.0224 1.0000 1.0000
0.000 0.0079 0.01500 0.00786 -0.0224 1.0000 1.0000
0.250 0.0495 0.01562 0.00834 -0.0261 0.9933 1.0000
0.500 0.0960 0.01625 0.00885 -0.0306 0.9840 1.0000
0.750 0.1404 0.01675 0.00926 -0.0345 0.9732 1.0000
1.000 0.1853 0.01719 0.00965 -0.0384 0.9616 1.0000
1.250 0.2316 0.01752 0.00995 -0.0424 0.9491 1.0000
1.500 0.2783 0.01774 0.01016 -0.0462 0.9361 1.0000
1.750 0.3246 0.01782 0.01028 -0.0497 0.9229 1.0000
2.000 0.3705 0.01780 0.01030 -0.0530 0.9101 1.0000
2.250 0.4166 0.01767 0.01024 -0.0561 0.8975 1.0000
2.500 0.4667 0.01737 0.01007 -0.0597 0.8861 1.0000
2.750 0.5155 0.01694 0.00976 -0.0629 0.8739 1.0000
3.000 0.5586 0.01645 0.00940 -0.0647 0.8602 1.0000
3.250 0.5986 0.01592 0.00905 -0.0658 0.8445 1.0000
3.500 0.6327 0.01546 0.00873 -0.0657 0.8246 1.0000
3.750 0.6719 0.01483 0.00822 -0.0662 0.8041 1.0000
4.000 0.7035 0.01438 0.00788 -0.0653 0.7757 1.0000
4.250 0.7303 0.01407 0.00767 -0.0636 0.7366 1.0000
4.500 0.7558 0.01387 0.00742 -0.0616 0.6818 1.0000
4.750 0.7783 0.01395 0.00725 -0.0592 0.6057 1.0000
5.000 0.7976 0.01450 0.00736 -0.0568 0.5191 1.0000
5.250 0.8159 0.01534 0.00778 -0.0547 0.4479 1.0000
5.500 0.8346 0.01621 0.00838 -0.0530 0.3916 1.0000
5.750 0.8534 0.01707 0.00902 -0.0514 0.3430 1.0000
6.000 0.8717 0.01795 0.00971 -0.0498 0.2957 1.0000
6.250 0.8882 0.01896 0.01047 -0.0480 0.2418 1.0000
6.500 0.9032 0.02034 0.01154 -0.0460 0.1802 1.0000
6.750 0.9196 0.02179 0.01275 -0.0442 0.1375 1.0000
7.000 0.9385 0.02342 0.01423 -0.0426 0.1136 1.0000
7.250 0.9583 0.02499 0.01571 -0.0414 0.0954 1.0000
7.500 0.9804 0.02696 0.01764 -0.0404 0.0820 1.0000
7.750 1.0027 0.02904 0.01983 -0.0395 0.0702 1.0000
8.000 1.0242 0.03137 0.02234 -0.0384 0.0604 1.0000
8.250 1.0482 0.03525 0.02622 -0.0381 0.0545 1.0000
8.500 1.0642 0.03722 0.02885 -0.0359 0.0500 1.0000
8.750 1.0809 0.03972 0.03160 -0.0344 0.0460 1.0000
9.000 1.0948 0.04326 0.03546 -0.0328 0.0444 1.0000
9.250 1.1039 0.04747 0.04008 -0.0308 0.0438 1.0000
9.500 1.1079 0.05161 0.04471 -0.0282 0.0439 1.0000
9.750 1.1026 0.05579 0.04952 -0.0248 0.0450 1.0000
10.000 1.0780 0.06124 0.05568 -0.0206 0.0471 1.0000
10.250 1.0567 0.06579 0.06058 -0.0175 0.0485 1.0000
10.500 1.0341 0.07007 0.06508 -0.0152 0.0495 1.0000
10.750 1.0107 0.07476 0.06996 -0.0144 0.0503 1.0000
11.000 0.9864 0.08011 0.07546 -0.0155 0.0510 1.0000
11.250 0.9628 0.08634 0.08179 -0.0184 0.0517 1.0000
11.500 0.9423 0.09346 0.08899 -0.0225 0.0526 1.0000
11.750 0.9322 0.10026 0.09579 -0.0255 0.0538 1.0000
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Polar data table (+)
Polar graphs
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