SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7062 (14%) (sd7062-il) Reynolds number: 50,000 Max Cl/Cd: 32.14 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7062-il-50000-n5.txt Download as CSV file: xf-sd7062-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7062 (14%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2807 0.10122 0.09419 -0.0436 1.0000 0.0631
-9.250 -0.2836 0.09780 0.09087 -0.0442 1.0000 0.0620
-9.000 -0.2904 0.09425 0.08744 -0.0449 1.0000 0.0609
-8.750 -0.3029 0.09041 0.08374 -0.0456 1.0000 0.0596
-8.500 -0.3381 0.08451 0.07802 -0.0479 1.0000 0.0575
-8.250 -0.3556 0.08241 0.07606 -0.0460 1.0000 0.0572
-8.000 -0.3788 0.08068 0.07447 -0.0435 1.0000 0.0569
-7.750 -0.3997 0.07780 0.07169 -0.0433 0.9982 0.0564
-7.500 -0.3919 0.06968 0.06342 -0.0542 0.9835 0.0558
-7.250 -0.3859 0.06241 0.05584 -0.0629 0.9696 0.0557
-7.000 -0.3763 0.05607 0.04906 -0.0693 0.9567 0.0560
-6.750 -0.3633 0.05083 0.04326 -0.0735 0.9443 0.0567
-6.500 -0.3446 0.04634 0.03807 -0.0766 0.9333 0.0576
-6.250 -0.3139 0.04353 0.03505 -0.0793 0.9255 0.0588
-6.000 -0.2893 0.04108 0.03228 -0.0804 0.9151 0.0597
-5.750 -0.2546 0.03852 0.02934 -0.0830 0.9082 0.0612
-5.500 -0.2284 0.03656 0.02702 -0.0835 0.8978 0.0631
-5.250 -0.1928 0.03452 0.02451 -0.0853 0.8908 0.0666
-5.000 -0.1669 0.03338 0.02336 -0.0854 0.8803 0.0700
-4.750 -0.1316 0.03191 0.02162 -0.0865 0.8731 0.0743
-4.500 -0.1060 0.03082 0.02045 -0.0861 0.8625 0.0784
-4.250 -0.0720 0.02973 0.01919 -0.0869 0.8551 0.0868
-4.000 -0.0480 0.02890 0.01839 -0.0863 0.8441 0.0960
-3.750 -0.0151 0.02786 0.01730 -0.0870 0.8367 0.1135
-3.500 0.0078 0.02706 0.01665 -0.0864 0.8253 0.1377
-3.250 0.0408 0.02595 0.01577 -0.0874 0.8180 0.1923
-3.000 0.0622 0.02527 0.01545 -0.0867 0.8063 0.2616
-2.750 0.0922 0.02453 0.01511 -0.0868 0.7989 0.3564
-2.500 0.1125 0.02433 0.01515 -0.0853 0.7871 0.4334
-2.250 0.1380 0.02410 0.01507 -0.0840 0.7782 0.5071
-2.000 0.1607 0.02400 0.01506 -0.0823 0.7679 0.5689
-1.750 0.1829 0.02393 0.01504 -0.0804 0.7581 0.6238
-1.500 0.2061 0.02380 0.01496 -0.0783 0.7489 0.6752
-1.250 0.2255 0.02378 0.01498 -0.0757 0.7384 0.7222
-1.000 0.2497 0.02359 0.01476 -0.0736 0.7300 0.7713
-0.750 0.2694 0.02359 0.01478 -0.0712 0.7190 0.8192
-0.500 0.3042 0.02331 0.01439 -0.0710 0.7114 0.8743
-0.250 0.3496 0.02327 0.01424 -0.0739 0.6997 0.9342
0.000 0.4093 0.02301 0.01372 -0.0797 0.6906 1.0000
0.250 0.4273 0.02321 0.01371 -0.0786 0.6794 1.0000
0.500 0.4492 0.02343 0.01372 -0.0779 0.6688 1.0000
0.750 0.4765 0.02349 0.01355 -0.0776 0.6597 1.0000
1.000 0.4980 0.02383 0.01374 -0.0769 0.6482 1.0000
1.250 0.5279 0.02383 0.01352 -0.0768 0.6401 1.0000
1.750 0.5747 0.02447 0.01390 -0.0755 0.6182 1.0000
2.000 0.6014 0.02464 0.01394 -0.0751 0.6085 1.0000
2.250 0.6242 0.02503 0.01423 -0.0744 0.5974 1.0000
2.500 0.6541 0.02506 0.01411 -0.0742 0.5892 1.0000
2.750 0.6748 0.02558 0.01457 -0.0733 0.5774 1.0000
3.000 0.7013 0.02581 0.01469 -0.0729 0.5680 1.0000
3.250 0.7260 0.02613 0.01494 -0.0723 0.5577 1.0000
3.500 0.7489 0.02656 0.01532 -0.0715 0.5472 1.0000
3.750 0.7773 0.02670 0.01534 -0.0712 0.5384 1.0000
4.000 0.7975 0.02730 0.01594 -0.0703 0.5271 1.0000
4.250 0.8254 0.02747 0.01601 -0.0699 0.5185 1.0000
4.500 0.8464 0.02803 0.01657 -0.0690 0.5075 1.0000
4.750 0.8696 0.02848 0.01699 -0.0683 0.4978 1.0000
5.000 0.8951 0.02879 0.01726 -0.0678 0.4884 1.0000
5.250 0.9148 0.02946 0.01795 -0.0668 0.4779 1.0000
5.500 0.9435 0.02961 0.01800 -0.0665 0.4697 1.0000
5.750 0.9599 0.03045 0.01892 -0.0652 0.4586 1.0000
6.000 0.9860 0.03078 0.01919 -0.0647 0.4503 1.0000
6.250 1.0043 0.03151 0.01997 -0.0636 0.4400 1.0000
6.500 1.0257 0.03210 0.02056 -0.0628 0.4309 1.0000
6.750 1.0475 0.03266 0.02114 -0.0620 0.4218 1.0000
7.000 1.0649 0.03348 0.02201 -0.0608 0.4123 1.0000
7.250 1.0891 0.03389 0.02239 -0.0602 0.4038 1.0000
7.500 1.1025 0.03496 0.02357 -0.0587 0.3944 1.0000
7.750 1.1283 0.03527 0.02384 -0.0582 0.3864 1.0000
8.000 1.1374 0.03657 0.02526 -0.0564 0.3770 1.0000
8.250 1.1645 0.03684 0.02550 -0.0560 0.3695 1.0000
8.500 1.1689 0.03838 0.02719 -0.0539 0.3602 1.0000
8.750 1.1964 0.03860 0.02736 -0.0535 0.3529 1.0000
9.000 1.1956 0.04043 0.02937 -0.0511 0.3442 1.0000
9.250 1.2216 0.04073 0.02964 -0.0506 0.3369 1.0000
9.500 1.2154 0.04276 0.03185 -0.0477 0.3290 1.0000
9.750 1.2354 0.04338 0.03247 -0.0468 0.3218 1.0000
10.000 1.2327 0.04544 0.03466 -0.0446 0.3146 1.0000
10.250 1.2409 0.04684 0.03613 -0.0432 0.3073 1.0000
10.500 1.2497 0.04828 0.03764 -0.0419 0.3006 1.0000
10.750 1.2369 0.05145 0.04098 -0.0402 0.2934 1.0000
11.000 1.2755 0.05062 0.04007 -0.0399 0.2874 1.0000
11.250 1.2232 0.05761 0.04737 -0.0384 0.2801 1.0000
11.500 1.2467 0.05780 0.04758 -0.0376 0.2740 1.0000
11.750 1.2018 0.06549 0.05546 -0.0381 0.2668 1.0000
12.000 1.1841 0.07072 0.06081 -0.0387 0.2598 1.0000
12.250 1.2475 0.06584 0.05587 -0.0363 0.2558 1.0000
12.500 1.1190 0.08701 0.07731 -0.0433 0.2433 1.0000
12.750 1.1718 0.08214 0.07249 -0.0402 0.2412 1.0000
13.000 1.0727 0.10259 0.09303 -0.0488 0.2272 1.0000
13.250 1.1107 0.09941 0.08992 -0.0462 0.2254 1.0000
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Polar data table (+)
Polar graphs
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