SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD5060 (9.5%) (sd5060-il) Reynolds number: 100,000 Max Cl/Cd: 50.23 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd5060-il-100000-n5.txt Download as CSV file: xf-sd5060-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD5060 (9.5%)
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5173 0.08967 0.08471 -0.0195 1.0000 0.0293
-9.500 -0.5258 0.08285 0.07796 -0.0235 1.0000 0.0294
-9.250 -0.5353 0.07599 0.07116 -0.0277 1.0000 0.0293
-9.000 -0.5492 0.06812 0.06335 -0.0334 1.0000 0.0290
-8.750 -0.5681 0.05933 0.05459 -0.0423 1.0000 0.0284
-8.500 -0.5836 0.05195 0.04695 -0.0482 1.0000 0.0281
-8.250 -0.5909 0.04579 0.04036 -0.0514 1.0000 0.0284
-8.000 -0.5887 0.04082 0.03489 -0.0527 1.0000 0.0286
-7.750 -0.5800 0.03680 0.03035 -0.0530 1.0000 0.0289
-7.500 -0.5671 0.03355 0.02656 -0.0526 1.0000 0.0293
-7.250 -0.5519 0.03085 0.02347 -0.0518 1.0000 0.0298
-7.000 -0.5361 0.02862 0.02104 -0.0509 1.0000 0.0306
-6.750 -0.5191 0.02717 0.01948 -0.0498 1.0000 0.0319
-6.500 -0.5018 0.02598 0.01814 -0.0486 1.0000 0.0339
-6.250 -0.4845 0.02468 0.01662 -0.0472 1.0000 0.0357
-6.000 -0.4670 0.02336 0.01508 -0.0456 1.0000 0.0370
-5.750 -0.4493 0.02222 0.01373 -0.0441 1.0000 0.0382
-5.500 -0.4208 0.02088 0.01231 -0.0449 0.9952 0.0402
-5.250 -0.3864 0.01985 0.01119 -0.0467 0.9879 0.0438
-5.000 -0.3504 0.01894 0.01014 -0.0487 0.9814 0.0503
-4.750 -0.3158 0.01801 0.00912 -0.0503 0.9740 0.0604
-4.500 -0.2796 0.01704 0.00825 -0.0524 0.9679 0.0821
-4.250 -0.2451 0.01643 0.00772 -0.0540 0.9601 0.1165
-4.000 -0.2100 0.01602 0.00745 -0.0558 0.9531 0.1602
-3.750 -0.1762 0.01571 0.00717 -0.0572 0.9448 0.1991
-3.500 -0.1435 0.01538 0.00686 -0.0582 0.9366 0.2259
-3.250 -0.1102 0.01507 0.00657 -0.0593 0.9286 0.2542
-3.000 -0.0803 0.01479 0.00632 -0.0597 0.9190 0.2839
-2.750 -0.0490 0.01451 0.00609 -0.0602 0.9107 0.3175
-2.500 -0.0203 0.01423 0.00591 -0.0603 0.9009 0.3538
-2.250 0.0078 0.01398 0.00576 -0.0601 0.8909 0.3955
-2.000 0.0366 0.01371 0.00560 -0.0600 0.8822 0.4444
-1.750 0.0630 0.01346 0.00551 -0.0595 0.8717 0.4995
-1.500 0.0887 0.01322 0.00545 -0.0586 0.8614 0.5610
-1.250 0.1143 0.01297 0.00538 -0.0576 0.8520 0.6305
-1.000 0.1381 0.01273 0.00536 -0.0560 0.8416 0.7048
-0.750 0.1617 0.01252 0.00534 -0.0542 0.8308 0.7847
-0.500 0.1920 0.01232 0.00525 -0.0536 0.8212 0.8725
-0.250 0.2377 0.01214 0.00504 -0.0565 0.8113 0.9632
0.000 0.2716 0.01213 0.00492 -0.0576 0.7992 1.0000
0.250 0.2966 0.01219 0.00486 -0.0569 0.7868 1.0000
0.500 0.3218 0.01225 0.00481 -0.0561 0.7742 1.0000
0.750 0.3472 0.01231 0.00477 -0.0553 0.7613 1.0000
1.000 0.3727 0.01237 0.00474 -0.0546 0.7477 1.0000
1.250 0.3983 0.01244 0.00472 -0.0538 0.7332 1.0000
1.500 0.4239 0.01251 0.00471 -0.0531 0.7177 1.0000
1.750 0.4496 0.01259 0.00473 -0.0523 0.7014 1.0000
2.000 0.4754 0.01268 0.00475 -0.0516 0.6844 1.0000
2.250 0.5012 0.01277 0.00477 -0.0509 0.6668 1.0000
2.500 0.5270 0.01288 0.00480 -0.0501 0.6489 1.0000
2.750 0.5528 0.01301 0.00490 -0.0495 0.6285 1.0000
3.000 0.5785 0.01315 0.00497 -0.0488 0.6076 1.0000
3.250 0.6041 0.01331 0.00508 -0.0481 0.5849 1.0000
3.500 0.6296 0.01350 0.00520 -0.0474 0.5610 1.0000
3.750 0.6548 0.01372 0.00535 -0.0467 0.5343 1.0000
4.000 0.6799 0.01397 0.00552 -0.0460 0.5061 1.0000
4.250 0.7047 0.01427 0.00572 -0.0453 0.4760 1.0000
4.500 0.7291 0.01462 0.00598 -0.0446 0.4445 1.0000
4.750 0.7533 0.01501 0.00627 -0.0439 0.4111 1.0000
5.000 0.7771 0.01547 0.00660 -0.0432 0.3772 1.0000
5.250 0.8005 0.01598 0.00698 -0.0425 0.3447 1.0000
5.500 0.8237 0.01654 0.00744 -0.0418 0.3143 1.0000
5.750 0.8468 0.01712 0.00793 -0.0411 0.2866 1.0000
6.000 0.8698 0.01773 0.00846 -0.0405 0.2617 1.0000
6.250 0.8924 0.01838 0.00904 -0.0398 0.2405 1.0000
6.500 0.9152 0.01901 0.00968 -0.0391 0.2217 1.0000
6.750 0.9376 0.01968 0.01033 -0.0385 0.2050 1.0000
7.000 0.9599 0.02037 0.01102 -0.0378 0.1903 1.0000
7.250 0.9820 0.02108 0.01174 -0.0370 0.1773 1.0000
7.500 1.0037 0.02182 0.01250 -0.0363 0.1654 1.0000
7.750 1.0248 0.02261 0.01331 -0.0355 0.1547 1.0000
8.000 1.0459 0.02338 0.01414 -0.0348 0.1443 1.0000
8.250 1.0670 0.02416 0.01502 -0.0340 0.1342 1.0000
8.500 1.0870 0.02503 0.01594 -0.0331 0.1255 1.0000
8.750 1.1063 0.02590 0.01686 -0.0322 0.1166 1.0000
9.000 1.1259 0.02679 0.01793 -0.0313 0.1080 1.0000
9.250 1.1434 0.02779 0.01896 -0.0302 0.1005 1.0000
9.500 1.1613 0.02875 0.02008 -0.0292 0.0925 1.0000
9.750 1.1774 0.02988 0.02131 -0.0280 0.0858 1.0000
10.000 1.1926 0.03095 0.02250 -0.0268 0.0789 1.0000
10.250 1.2064 0.03223 0.02391 -0.0255 0.0728 1.0000
10.750 1.2277 0.03486 0.02681 -0.0223 0.0619 1.0000
11.000 1.2353 0.03626 0.02838 -0.0205 0.0569 1.0000
11.250 1.2379 0.03792 0.03002 -0.0186 0.0532 1.0000
11.500 1.2441 0.03964 0.03203 -0.0171 0.0485 1.0000
11.750 1.2462 0.04151 0.03402 -0.0159 0.0450 1.0000
12.000 1.2454 0.04382 0.03641 -0.0148 0.0419 1.0000
12.250 1.2461 0.04625 0.03908 -0.0141 0.0383 1.0000
12.500 1.2439 0.04894 0.04191 -0.0138 0.0358 1.0000
12.750 1.2381 0.05218 0.04521 -0.0140 0.0340 1.0000
13.000 1.2329 0.05579 0.04906 -0.0144 0.0320 1.0000
13.250 1.2260 0.05981 0.05331 -0.0152 0.0303 1.0000
13.500 1.2175 0.06421 0.05791 -0.0166 0.0290 1.0000
13.750 1.2076 0.06905 0.06291 -0.0187 0.0279 1.0000
14.000 1.1959 0.07444 0.06844 -0.0213 0.0271 1.0000
14.250 1.1829 0.08035 0.07450 -0.0243 0.0265 1.0000
14.500 1.1688 0.08675 0.08102 -0.0277 0.0260 1.0000
14.750 1.1548 0.09344 0.08786 -0.0313 0.0256 1.0000
15.000 1.1371 0.10149 0.09608 -0.0360 0.0254 1.0000
15.250 1.1186 0.11008 0.10486 -0.0410 0.0253 1.0000
15.500 1.0993 0.11925 0.11420 -0.0464 0.0253 1.0000
15.750 1.0802 0.12874 0.12383 -0.0519 0.0254 1.0000
16.000 1.0580 0.13958 0.13481 -0.0583 0.0255 1.0000
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Polar data table (+)
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