S2062 8% (s2062-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2062 8% (s2062-il) Reynolds number: 100,000 Max Cl/Cd: 49.87 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2062-il-100000-n5.txt Download as CSV file: xf-s2062-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2062 8%
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5046 0.08774 0.08269 -0.0245 1.0000 0.0200
-8.750 -0.5092 0.08276 0.07779 -0.0271 1.0000 0.0196
-8.500 -0.5162 0.07750 0.07262 -0.0299 1.0000 0.0193
-8.250 -0.5272 0.07180 0.06706 -0.0336 1.0000 0.0189
-8.000 -0.5511 0.05889 0.05407 -0.0434 1.0000 0.0176
-7.500 -0.5626 0.04754 0.04213 -0.0465 1.0000 0.0171
-7.250 -0.5608 0.04311 0.03734 -0.0463 1.0000 0.0170
-7.000 -0.5550 0.03886 0.03264 -0.0457 1.0000 0.0171
-6.750 -0.5450 0.03514 0.02841 -0.0448 1.0000 0.0171
-6.500 -0.5322 0.03185 0.02473 -0.0438 1.0000 0.0174
-6.250 -0.5164 0.02961 0.02218 -0.0428 1.0000 0.0182
-6.000 -0.4984 0.02798 0.02030 -0.0419 1.0000 0.0196
-5.750 -0.4791 0.02622 0.01820 -0.0408 1.0000 0.0216
-5.500 -0.4588 0.02423 0.01584 -0.0395 1.0000 0.0227
-5.250 -0.4379 0.02253 0.01383 -0.0383 1.0000 0.0237
-5.000 -0.4176 0.02082 0.01200 -0.0372 1.0000 0.0256
-4.750 -0.3964 0.01970 0.01077 -0.0362 1.0000 0.0282
-4.500 -0.3744 0.01865 0.00954 -0.0351 1.0000 0.0339
-4.250 -0.3525 0.01767 0.00851 -0.0343 1.0000 0.0469
-4.000 -0.3302 0.01691 0.00781 -0.0336 1.0000 0.0716
-3.750 -0.3079 0.01636 0.00735 -0.0330 1.0000 0.1007
-3.500 -0.2852 0.01584 0.00683 -0.0323 1.0000 0.1259
-3.250 -0.2625 0.01537 0.00641 -0.0316 1.0000 0.1533
-3.000 -0.2397 0.01494 0.00605 -0.0310 1.0000 0.1902
-2.750 -0.2107 0.01451 0.00578 -0.0317 0.9973 0.2420
-2.500 -0.1764 0.01406 0.00559 -0.0335 0.9919 0.3199
-2.250 -0.1427 0.01356 0.00546 -0.0351 0.9863 0.4227
-2.000 -0.1110 0.01305 0.00541 -0.0360 0.9806 0.5549
-1.750 -0.0825 0.01267 0.00551 -0.0356 0.9738 0.6976
-1.500 -0.0531 0.01254 0.00557 -0.0351 0.9672 0.8048
-1.250 -0.0196 0.01245 0.00555 -0.0354 0.9604 0.8882
-1.000 0.0353 0.01238 0.00538 -0.0406 0.9577 0.9681
-0.750 0.0780 0.01235 0.00521 -0.0439 0.9505 1.0000
-0.500 0.1180 0.01236 0.00510 -0.0465 0.9435 1.0000
-0.250 0.1527 0.01236 0.00499 -0.0480 0.9338 1.0000
0.000 0.1902 0.01234 0.00490 -0.0500 0.9253 1.0000
0.250 0.2265 0.01230 0.00481 -0.0517 0.9157 1.0000
0.500 0.2591 0.01227 0.00474 -0.0525 0.9041 1.0000
0.750 0.2917 0.01224 0.00468 -0.0533 0.8920 1.0000
1.000 0.3239 0.01220 0.00463 -0.0539 0.8791 1.0000
1.250 0.3551 0.01216 0.00460 -0.0543 0.8648 1.0000
1.500 0.3854 0.01212 0.00456 -0.0544 0.8492 1.0000
1.750 0.4153 0.01209 0.00453 -0.0544 0.8324 1.0000
2.000 0.4436 0.01208 0.00453 -0.0541 0.8133 1.0000
2.250 0.4712 0.01209 0.00458 -0.0536 0.7922 1.0000
2.500 0.4985 0.01211 0.00461 -0.0531 0.7692 1.0000
2.750 0.5256 0.01215 0.00465 -0.0524 0.7435 1.0000
3.000 0.5521 0.01224 0.00472 -0.0517 0.7141 1.0000
3.250 0.5780 0.01236 0.00484 -0.0508 0.6809 1.0000
3.500 0.6033 0.01254 0.00496 -0.0498 0.6433 1.0000
3.750 0.6279 0.01279 0.00512 -0.0488 0.6015 1.0000
4.000 0.6516 0.01312 0.00533 -0.0477 0.5557 1.0000
4.250 0.6747 0.01353 0.00564 -0.0465 0.5074 1.0000
4.500 0.6972 0.01400 0.00597 -0.0453 0.4567 1.0000
4.750 0.7192 0.01455 0.00636 -0.0442 0.4038 1.0000
5.000 0.7397 0.01526 0.00679 -0.0429 0.3405 1.0000
5.250 0.7591 0.01613 0.00730 -0.0417 0.2648 1.0000
5.500 0.7782 0.01716 0.00794 -0.0406 0.1868 1.0000
5.750 0.7983 0.01819 0.00865 -0.0397 0.1239 1.0000
6.000 0.8175 0.01945 0.00960 -0.0386 0.0706 1.0000
6.250 0.8366 0.02078 0.01074 -0.0374 0.0455 1.0000
6.500 0.8569 0.02191 0.01197 -0.0362 0.0379 1.0000
6.750 0.8764 0.02312 0.01327 -0.0350 0.0341 1.0000
7.000 0.8945 0.02450 0.01478 -0.0335 0.0319 1.0000
7.250 0.9139 0.02583 0.01634 -0.0322 0.0304 1.0000
7.500 0.9334 0.02732 0.01800 -0.0309 0.0292 1.0000
7.750 0.9536 0.02895 0.01979 -0.0298 0.0280 1.0000
8.000 0.9735 0.03049 0.02148 -0.0288 0.0262 1.0000
8.250 0.9917 0.03226 0.02332 -0.0279 0.0243 1.0000
8.500 1.0100 0.03485 0.02611 -0.0269 0.0234 1.0000
8.750 1.0280 0.03725 0.02887 -0.0257 0.0229 1.0000
9.000 1.0431 0.04001 0.03204 -0.0242 0.0225 1.0000
9.250 1.0543 0.04307 0.03559 -0.0225 0.0222 1.0000
9.500 1.0607 0.04644 0.03941 -0.0206 0.0220 1.0000
9.750 1.0622 0.04999 0.04341 -0.0185 0.0218 1.0000
10.000 1.0582 0.05367 0.04749 -0.0162 0.0217 1.0000
10.250 1.0484 0.05721 0.05137 -0.0138 0.0215 1.0000
10.500 1.0333 0.06070 0.05514 -0.0114 0.0214 1.0000
10.750 1.0155 0.06463 0.05931 -0.0103 0.0213 1.0000
11.000 0.9963 0.06921 0.06411 -0.0108 0.0214 1.0000
11.250 0.9754 0.07475 0.06983 -0.0130 0.0216 1.0000
11.500 0.9545 0.08136 0.07659 -0.0171 0.0219 1.0000
11.750 0.9331 0.08944 0.08479 -0.0230 0.0222 1.0000
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Polar data table (+)
Polar graphs
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