S2048 (s2048-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2048 (s2048-il) Reynolds number: 200,000 Max Cl/Cd: 75.75 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2048-il-200000.txt Download as CSV file: xf-s2048-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4596 0.11059 0.10687 -0.0281 1.0000 0.0411
-10.000 -0.4636 0.10704 0.10338 -0.0319 1.0000 0.0416
-9.750 -0.4646 0.10337 0.09975 -0.0344 1.0000 0.0418
-9.500 -0.4656 0.09960 0.09602 -0.0365 1.0000 0.0419
-9.250 -0.4686 0.09549 0.09196 -0.0390 1.0000 0.0419
-9.000 -0.4625 0.09068 0.08717 -0.0339 1.0000 0.0439
-8.750 -0.4586 0.08799 0.08450 -0.0331 1.0000 0.0452
-8.500 -0.4593 0.08490 0.08145 -0.0335 1.0000 0.0461
-8.250 -0.4631 0.08170 0.07830 -0.0340 1.0000 0.0475
-8.000 -0.4715 0.07847 0.07514 -0.0345 1.0000 0.0479
-7.750 -0.4858 0.07526 0.07201 -0.0348 1.0000 0.0486
-7.500 -0.4961 0.07085 0.06764 -0.0379 1.0000 0.0493
-7.250 -0.5045 0.06670 0.06346 -0.0395 1.0000 0.0502
-7.000 -0.5119 0.06232 0.05897 -0.0412 1.0000 0.0523
-6.750 -0.5190 0.06004 0.05615 -0.0423 1.0000 0.0544
-6.500 -0.5229 0.05319 0.04925 -0.0421 1.0000 0.0556
-6.250 -0.4907 0.03957 0.03622 -0.0373 1.0000 0.0577
-6.000 -0.4864 0.03688 0.03347 -0.0361 1.0000 0.0598
-5.750 -0.4804 0.03392 0.03032 -0.0356 1.0000 0.0638
-5.500 -0.4745 0.02970 0.02572 -0.0359 1.0000 0.0703
-5.250 -0.4625 0.02757 0.02360 -0.0349 1.0000 0.0741
-5.000 -0.4435 0.02394 0.01947 -0.0362 0.9989 0.0836
-4.750 -0.4226 0.02632 0.02012 -0.0360 1.0000 0.0399
-4.500 -0.3987 0.02324 0.01660 -0.0355 1.0000 0.0384
-4.250 -0.3746 0.02154 0.01452 -0.0348 1.0000 0.0393
-4.000 -0.3482 0.02025 0.01292 -0.0345 0.9995 0.0407
-3.750 -0.3127 0.01870 0.01111 -0.0358 0.9968 0.0413
-3.500 -0.2773 0.01729 0.00954 -0.0372 0.9944 0.0426
-3.250 -0.2441 0.01608 0.00836 -0.0386 0.9909 0.0467
-3.000 -0.2086 0.01547 0.00770 -0.0403 0.9870 0.0521
-2.750 -0.1714 0.01467 0.00690 -0.0425 0.9839 0.0608
-2.500 -0.1382 0.01350 0.00614 -0.0440 0.9799 0.1447
-2.250 -0.1098 0.01183 0.00612 -0.0454 0.9758 0.5328
-2.000 -0.0765 0.01170 0.00637 -0.0463 0.9716 0.6731
-1.750 -0.0477 0.01167 0.00650 -0.0462 0.9657 0.7380
-1.500 -0.0171 0.01167 0.00659 -0.0463 0.9600 0.7897
-1.250 0.0199 0.01169 0.00662 -0.0478 0.9563 0.8229
-1.000 0.0432 0.01160 0.00658 -0.0464 0.9479 0.8583
-0.750 0.0765 0.01151 0.00657 -0.0466 0.9436 0.9080
-0.500 0.1233 0.01143 0.00650 -0.0499 0.9395 0.9597
-0.250 0.1808 0.01129 0.00629 -0.0561 0.9353 0.9915
0.000 0.2342 0.01107 0.00600 -0.0613 0.9308 1.0000
0.250 0.2743 0.01080 0.00568 -0.0639 0.9219 1.0000
0.500 0.3223 0.01045 0.00528 -0.0677 0.9164 1.0000
0.750 0.3539 0.01024 0.00504 -0.0684 0.9065 1.0000
1.000 0.3951 0.00995 0.00473 -0.0708 0.9011 1.0000
1.250 0.4228 0.00981 0.00457 -0.0706 0.8901 1.0000
1.500 0.4526 0.00966 0.00442 -0.0707 0.8797 1.0000
1.750 0.4839 0.00949 0.00425 -0.0710 0.8697 1.0000
2.000 0.5147 0.00933 0.00410 -0.0712 0.8585 1.0000
2.250 0.5431 0.00923 0.00400 -0.0709 0.8450 1.0000
2.500 0.5698 0.00918 0.00396 -0.0702 0.8293 1.0000
2.750 0.5962 0.00916 0.00394 -0.0695 0.8114 1.0000
3.000 0.6231 0.00914 0.00393 -0.0689 0.7919 1.0000
3.250 0.6488 0.00917 0.00395 -0.0680 0.7686 1.0000
3.500 0.6741 0.00922 0.00397 -0.0670 0.7403 1.0000
3.750 0.6980 0.00931 0.00398 -0.0657 0.7009 1.0000
4.000 0.7204 0.00951 0.00402 -0.0641 0.6433 1.0000
4.250 0.7404 0.00994 0.00411 -0.0622 0.5661 1.0000
4.500 0.7583 0.01060 0.00435 -0.0602 0.4831 1.0000
4.750 0.7768 0.01131 0.00472 -0.0585 0.4143 1.0000
5.000 0.7967 0.01198 0.00513 -0.0571 0.3602 1.0000
5.250 0.8176 0.01260 0.00559 -0.0560 0.3169 1.0000
5.500 0.8392 0.01318 0.00604 -0.0551 0.2799 1.0000
5.750 0.8610 0.01375 0.00650 -0.0541 0.2444 1.0000
6.000 0.8822 0.01438 0.00699 -0.0532 0.2019 1.0000
6.250 0.9017 0.01526 0.00759 -0.0520 0.1440 1.0000
6.500 0.9194 0.01646 0.00849 -0.0505 0.0988 1.0000
6.750 0.9369 0.01769 0.00961 -0.0489 0.0784 1.0000
7.000 0.9555 0.01885 0.01076 -0.0474 0.0654 1.0000
7.250 0.9735 0.02013 0.01200 -0.0460 0.0543 1.0000
7.500 0.9944 0.02098 0.01295 -0.0449 0.0452 1.0000
7.750 1.0132 0.02229 0.01435 -0.0435 0.0370 1.0000
8.000 1.0299 0.02453 0.01659 -0.0419 0.0314 1.0000
8.250 1.0514 0.02610 0.01840 -0.0407 0.0283 1.0000
8.500 1.0714 0.02771 0.02015 -0.0395 0.0255 1.0000
8.750 1.0885 0.03126 0.02384 -0.0386 0.0227 1.0000
9.000 1.1059 0.03283 0.02573 -0.0369 0.0216 1.0000
9.250 1.1208 0.03547 0.02876 -0.0351 0.0209 1.0000
9.500 1.1312 0.03862 0.03233 -0.0329 0.0204 1.0000
9.750 1.1362 0.04217 0.03631 -0.0302 0.0203 1.0000
10.000 1.1351 0.04597 0.04054 -0.0272 0.0203 1.0000
10.250 1.1289 0.04986 0.04480 -0.0241 0.0206 1.0000
10.500 1.1161 0.05345 0.04870 -0.0204 0.0208 1.0000
10.750 1.0989 0.05708 0.05258 -0.0170 0.0211 1.0000
11.000 1.0796 0.06095 0.05668 -0.0146 0.0213 1.0000
11.250 1.0595 0.06521 0.06115 -0.0136 0.0214 1.0000
11.500 1.0384 0.07008 0.06621 -0.0140 0.0216 1.0000
11.750 1.0169 0.07575 0.07203 -0.0160 0.0218 1.0000
12.000 0.9944 0.08241 0.07884 -0.0196 0.0220 1.0000
12.250 0.9718 0.09038 0.08693 -0.0246 0.0223 1.0000
12.500 0.8525 0.09697 0.09386 -0.0270 0.0224 1.0000
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Polar data table (+)
Polar graphs
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