S3010-103-84 (s3010-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S3010-103-84 (s3010-il) Reynolds number: 200,000 Max Cl/Cd: 70.04 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s3010-il-200000.txt Download as CSV file: xf-s3010-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S3010-103-84
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4013 0.08842 0.08504 -0.0215 1.0000 0.0559
-8.250 -0.4014 0.08462 0.08129 -0.0242 1.0000 0.0580
-8.000 -0.4157 0.07953 0.07631 -0.0316 1.0000 0.0603
-7.750 -0.4361 0.07152 0.06819 -0.0460 1.0000 0.0610
-7.500 -0.4347 0.06562 0.06236 -0.0469 1.0000 0.0620
-7.250 -0.4211 0.06404 0.06090 -0.0439 1.0000 0.0631
-7.000 -0.4140 0.06187 0.05877 -0.0430 1.0000 0.0644
-6.750 -0.4159 0.05934 0.05625 -0.0423 1.0000 0.0657
-6.500 -0.4280 0.05721 0.05412 -0.0400 1.0000 0.0666
-6.250 -0.4153 0.04874 0.04502 -0.0504 0.9923 0.0747
-6.000 -0.3827 0.04550 0.04188 -0.0532 0.9868 0.0769
-5.750 -0.3519 0.02903 0.02354 -0.0595 0.9773 0.0395
-5.500 -0.3128 0.02556 0.01956 -0.0627 0.9725 0.0393
-5.250 -0.2769 0.02249 0.01606 -0.0647 0.9655 0.0380
-5.000 -0.2378 0.02010 0.01326 -0.0669 0.9598 0.0374
-4.750 -0.2026 0.01847 0.01137 -0.0680 0.9515 0.0379
-4.500 -0.1661 0.01715 0.00989 -0.0693 0.9442 0.0391
-4.250 -0.1363 0.01625 0.00887 -0.0692 0.9332 0.0404
-4.000 -0.1091 0.01516 0.00782 -0.0690 0.9223 0.0443
-3.750 -0.0821 0.01455 0.00715 -0.0683 0.9118 0.0488
-3.500 -0.0581 0.01373 0.00634 -0.0672 0.8997 0.0553
-3.250 -0.0343 0.01284 0.00555 -0.0660 0.8874 0.0867
-3.000 -0.0111 0.01195 0.00513 -0.0652 0.8757 0.1843
-2.750 0.0130 0.01148 0.00490 -0.0643 0.8647 0.2608
-2.500 0.0365 0.01096 0.00476 -0.0633 0.8530 0.3662
-2.250 0.0599 0.01051 0.00467 -0.0623 0.8407 0.4741
-2.000 0.0834 0.01016 0.00459 -0.0610 0.8289 0.5658
-1.750 0.1062 0.00985 0.00452 -0.0593 0.8178 0.6534
-1.500 0.1281 0.00959 0.00446 -0.0572 0.8061 0.7381
-1.250 0.1489 0.00939 0.00443 -0.0548 0.7937 0.8159
-1.000 0.1721 0.00925 0.00434 -0.0526 0.7817 0.8877
-0.750 0.2117 0.00913 0.00414 -0.0541 0.7700 0.9532
-0.500 0.2656 0.00902 0.00384 -0.0590 0.7576 0.9994
-0.250 0.2892 0.00907 0.00373 -0.0582 0.7438 1.0000
0.000 0.3137 0.00913 0.00365 -0.0574 0.7300 1.0000
0.250 0.3389 0.00920 0.00358 -0.0568 0.7163 1.0000
0.500 0.3646 0.00928 0.00353 -0.0562 0.7026 1.0000
0.750 0.3907 0.00937 0.00349 -0.0557 0.6890 1.0000
1.000 0.4170 0.00947 0.00347 -0.0552 0.6753 1.0000
1.250 0.4434 0.00958 0.00346 -0.0547 0.6615 1.0000
1.500 0.4700 0.00970 0.00346 -0.0543 0.6475 1.0000
1.750 0.4967 0.00982 0.00347 -0.0539 0.6333 1.0000
2.000 0.5234 0.00996 0.00350 -0.0535 0.6189 1.0000
2.250 0.5502 0.01010 0.00356 -0.0531 0.6041 1.0000
2.500 0.5770 0.01025 0.00363 -0.0528 0.5894 1.0000
2.750 0.6037 0.01040 0.00372 -0.0525 0.5746 1.0000
3.000 0.6305 0.01057 0.00382 -0.0522 0.5597 1.0000
3.250 0.6572 0.01075 0.00395 -0.0518 0.5449 1.0000
3.500 0.6839 0.01094 0.00407 -0.0515 0.5298 1.0000
3.750 0.7105 0.01114 0.00421 -0.0512 0.5147 1.0000
4.000 0.7369 0.01135 0.00438 -0.0509 0.4993 1.0000
4.250 0.7633 0.01158 0.00455 -0.0505 0.4838 1.0000
4.500 0.7896 0.01181 0.00473 -0.0502 0.4682 1.0000
4.750 0.8157 0.01206 0.00493 -0.0499 0.4524 1.0000
5.000 0.8416 0.01232 0.00516 -0.0495 0.4365 1.0000
5.250 0.8674 0.01260 0.00539 -0.0491 0.4203 1.0000
5.500 0.8930 0.01289 0.00565 -0.0488 0.4037 1.0000
5.750 0.9185 0.01318 0.00595 -0.0484 0.3866 1.0000
6.000 0.9437 0.01349 0.00625 -0.0480 0.3692 1.0000
6.250 0.9687 0.01383 0.00657 -0.0475 0.3519 1.0000
6.500 0.9933 0.01420 0.00692 -0.0471 0.3345 1.0000
6.750 1.0176 0.01460 0.00728 -0.0466 0.3173 1.0000
7.000 1.0414 0.01505 0.00767 -0.0461 0.3001 1.0000
7.250 1.0651 0.01550 0.00811 -0.0455 0.2829 1.0000
7.500 1.0884 0.01597 0.00860 -0.0450 0.2656 1.0000
7.750 1.1113 0.01649 0.00910 -0.0443 0.2488 1.0000
8.000 1.1336 0.01704 0.00964 -0.0437 0.2325 1.0000
8.250 1.1554 0.01763 0.01023 -0.0430 0.2168 1.0000
8.500 1.1766 0.01826 0.01084 -0.0422 0.2017 1.0000
8.750 1.1973 0.01893 0.01151 -0.0414 0.1874 1.0000
9.000 1.2173 0.01964 0.01222 -0.0405 0.1738 1.0000
9.250 1.2365 0.02040 0.01300 -0.0395 0.1612 1.0000
9.500 1.2547 0.02123 0.01382 -0.0385 0.1494 1.0000
9.750 1.2716 0.02213 0.01471 -0.0373 0.1387 1.0000
10.000 1.2878 0.02304 0.01562 -0.0360 0.1287 1.0000
10.250 1.3039 0.02392 0.01660 -0.0347 0.1193 1.0000
10.500 1.3170 0.02504 0.01772 -0.0331 0.1112 1.0000
10.750 1.3292 0.02602 0.01875 -0.0315 0.1038 1.0000
11.000 1.3386 0.02714 0.01994 -0.0294 0.0970 1.0000
11.250 1.3458 0.02823 0.02104 -0.0274 0.0907 1.0000
11.500 1.3534 0.02942 0.02234 -0.0256 0.0845 1.0000
11.750 1.3592 0.03070 0.02365 -0.0239 0.0790 1.0000
12.000 1.3649 0.03222 0.02528 -0.0225 0.0739 1.0000
12.250 1.3709 0.03373 0.02690 -0.0213 0.0694 1.0000
12.500 1.3723 0.03585 0.02897 -0.0201 0.0655 1.0000
12.750 1.3779 0.03758 0.03093 -0.0193 0.0614 1.0000
13.000 1.3800 0.03968 0.03310 -0.0188 0.0577 1.0000
13.250 1.3793 0.04230 0.03576 -0.0182 0.0543 1.0000
13.500 1.3805 0.04477 0.03843 -0.0181 0.0505 1.0000
13.750 1.3779 0.04774 0.04144 -0.0183 0.0473 1.0000
14.000 1.3740 0.05108 0.04489 -0.0184 0.0443 1.0000
14.250 1.3705 0.05453 0.04849 -0.0191 0.0410 1.0000
14.500 1.3647 0.05831 0.05232 -0.0200 0.0386 1.0000
14.750 1.3576 0.06244 0.05657 -0.0207 0.0362 1.0000
15.000 1.3519 0.06657 0.06087 -0.0220 0.0341 1.0000
15.250 1.3460 0.07085 0.06523 -0.0236 0.0324 1.0000
15.500 1.3407 0.07499 0.06937 -0.0248 0.0309 1.0000
15.750 1.3348 0.07950 0.07403 -0.0261 0.0297 1.0000
16.000 1.3262 0.08477 0.07951 -0.0285 0.0286 1.0000
16.250 1.3190 0.08989 0.08479 -0.0309 0.0275 1.0000
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Polar data table (+)
Polar graphs
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