S2048 (s2048-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2048 (s2048-il) Reynolds number: 100,000 Max Cl/Cd: 52.74 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2048-il-100000-n5.txt Download as CSV file: xf-s2048-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3752 0.08999 0.08519 -0.0330 1.0000 0.0326
-9.250 -0.3799 0.08527 0.08051 -0.0342 1.0000 0.0312
-9.000 -0.3878 0.07993 0.07524 -0.0359 1.0000 0.0299
-8.500 -0.4842 0.07726 0.07243 -0.0424 1.0000 0.0270
-8.250 -0.4941 0.07346 0.06870 -0.0432 1.0000 0.0267
-8.000 -0.5040 0.06921 0.06447 -0.0446 1.0000 0.0264
-7.750 -0.5116 0.06523 0.06046 -0.0453 1.0000 0.0261
-7.500 -0.5186 0.06103 0.05620 -0.0456 1.0000 0.0258
-7.250 -0.5231 0.05685 0.05190 -0.0455 1.0000 0.0256
-7.000 -0.5247 0.05268 0.04755 -0.0451 1.0000 0.0254
-6.750 -0.5231 0.04845 0.04307 -0.0446 1.0000 0.0252
-6.500 -0.5181 0.04425 0.03854 -0.0439 1.0000 0.0252
-6.250 -0.5095 0.04016 0.03404 -0.0431 1.0000 0.0253
-6.000 -0.4972 0.03641 0.02981 -0.0422 1.0000 0.0255
-5.750 -0.4808 0.03356 0.02634 -0.0412 1.0000 0.0269
-5.500 -0.4650 0.03063 0.02310 -0.0406 1.0000 0.0287
-5.250 -0.4458 0.02849 0.02064 -0.0398 1.0000 0.0297
-5.000 -0.4249 0.02641 0.01820 -0.0389 1.0000 0.0303
-4.750 -0.4030 0.02464 0.01606 -0.0380 1.0000 0.0312
-4.500 -0.3806 0.02313 0.01428 -0.0371 1.0000 0.0324
-4.250 -0.3496 0.02175 0.01266 -0.0378 0.9973 0.0344
-4.000 -0.3162 0.02090 0.01157 -0.0391 0.9940 0.0384
-3.750 -0.2857 0.01962 0.01027 -0.0400 0.9903 0.0408
-3.500 -0.2536 0.01875 0.00932 -0.0411 0.9864 0.0436
-3.250 -0.2197 0.01805 0.00845 -0.0425 0.9829 0.0484
-3.000 -0.1889 0.01735 0.00770 -0.0434 0.9781 0.0573
-2.750 -0.1565 0.01666 0.00709 -0.0447 0.9736 0.0898
-2.500 -0.1240 0.01559 0.00674 -0.0466 0.9702 0.2310
-2.250 -0.1018 0.01424 0.00694 -0.0460 0.9652 0.5800
-2.000 -0.0731 0.01413 0.00694 -0.0458 0.9597 0.6689
-1.750 -0.0422 0.01411 0.00696 -0.0460 0.9552 0.7295
-1.500 -0.0184 0.01404 0.00696 -0.0446 0.9480 0.7795
-1.250 0.0091 0.01398 0.00697 -0.0437 0.9432 0.8372
-1.000 0.0340 0.01389 0.00691 -0.0423 0.9363 0.8884
-0.750 0.0741 0.01385 0.00681 -0.0446 0.9321 0.9253
-0.500 0.1236 0.01382 0.00667 -0.0492 0.9293 0.9580
-0.250 0.1651 0.01376 0.00651 -0.0524 0.9226 1.0000
0.000 0.2032 0.01373 0.00637 -0.0548 0.9165 1.0000
0.250 0.2348 0.01369 0.00625 -0.0558 0.9071 1.0000
0.500 0.2744 0.01358 0.00608 -0.0581 0.9002 1.0000
0.750 0.3082 0.01345 0.00590 -0.0591 0.8894 1.0000
1.000 0.3414 0.01330 0.00571 -0.0599 0.8772 1.0000
1.250 0.3743 0.01315 0.00554 -0.0606 0.8644 1.0000
1.500 0.4065 0.01302 0.00540 -0.0611 0.8513 1.0000
1.750 0.4378 0.01292 0.00530 -0.0615 0.8377 1.0000
2.000 0.4686 0.01285 0.00524 -0.0617 0.8235 1.0000
2.250 0.4990 0.01280 0.00522 -0.0619 0.8081 1.0000
2.500 0.5294 0.01275 0.00519 -0.0620 0.7917 1.0000
2.750 0.5570 0.01277 0.00524 -0.0616 0.7717 1.0000
3.000 0.5860 0.01277 0.00529 -0.0614 0.7504 1.0000
3.250 0.6131 0.01282 0.00536 -0.0608 0.7245 1.0000
3.500 0.6402 0.01289 0.00543 -0.0603 0.6941 1.0000
3.750 0.6661 0.01301 0.00552 -0.0594 0.6554 1.0000
4.000 0.6915 0.01321 0.00562 -0.0585 0.6066 1.0000
4.250 0.7152 0.01356 0.00580 -0.0573 0.5453 1.0000
4.500 0.7362 0.01413 0.00604 -0.0557 0.4760 1.0000
4.750 0.7561 0.01482 0.00641 -0.0542 0.4119 1.0000
5.000 0.7762 0.01553 0.00687 -0.0529 0.3588 1.0000
5.250 0.7971 0.01621 0.00736 -0.0518 0.3146 1.0000
5.500 0.8182 0.01687 0.00790 -0.0508 0.2772 1.0000
5.750 0.8398 0.01752 0.00853 -0.0499 0.2415 1.0000
6.000 0.8610 0.01822 0.00913 -0.0489 0.2052 1.0000
6.250 0.8819 0.01897 0.00979 -0.0480 0.1678 1.0000
6.500 0.9020 0.01988 0.01053 -0.0470 0.1264 1.0000
6.750 0.9213 0.02094 0.01145 -0.0458 0.0977 1.0000
7.000 0.9402 0.02206 0.01254 -0.0446 0.0798 1.0000
7.250 0.9589 0.02319 0.01369 -0.0433 0.0667 1.0000
7.500 0.9765 0.02448 0.01512 -0.0418 0.0585 1.0000
7.750 0.9930 0.02586 0.01650 -0.0404 0.0502 1.0000
8.000 1.0118 0.02705 0.01790 -0.0391 0.0429 1.0000
8.250 1.0281 0.02850 0.01946 -0.0376 0.0361 1.0000
8.500 1.0448 0.02986 0.02096 -0.0363 0.0304 1.0000
8.750 1.0594 0.03166 0.02291 -0.0347 0.0260 1.0000
9.000 1.0752 0.03343 0.02492 -0.0331 0.0225 1.0000
9.250 1.0890 0.03537 0.02703 -0.0315 0.0207 1.0000
9.500 1.1001 0.03788 0.02969 -0.0298 0.0193 1.0000
9.750 1.1104 0.04104 0.03323 -0.0280 0.0184 1.0000
10.000 1.1181 0.04392 0.03653 -0.0259 0.0176 1.0000
10.250 1.1208 0.04666 0.03967 -0.0234 0.0166 1.0000
10.500 1.1185 0.04933 0.04266 -0.0207 0.0158 1.0000
10.750 1.1132 0.05202 0.04563 -0.0181 0.0152 1.0000
11.000 1.1053 0.05492 0.04879 -0.0159 0.0147 1.0000
11.250 1.0950 0.05812 0.05224 -0.0144 0.0143 1.0000
11.500 1.0824 0.06179 0.05615 -0.0136 0.0141 1.0000
11.750 1.0646 0.06664 0.06126 -0.0140 0.0142 1.0000
12.000 1.0462 0.07198 0.06683 -0.0157 0.0141 1.0000
12.250 1.0215 0.07927 0.07436 -0.0194 0.0144 1.0000
12.500 0.9888 0.08980 0.08515 -0.0264 0.0152 1.0000
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Polar data table (+)
Polar graphs
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