SG6051 (sg6051-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SG6051 (sg6051-il) Reynolds number: 200,000 Max Cl/Cd: 78.4 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sg6051-il-200000-n5.txt Download as CSV file: xf-sg6051-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SG6051
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4654 0.08422 0.08085 -0.0487 1.0000 0.0119
-9.750 -0.4829 0.07678 0.07350 -0.0531 1.0000 0.0118
-9.250 -0.5837 0.03711 0.03260 -0.0822 0.9559 0.0109
-9.000 -0.5775 0.03190 0.02670 -0.0825 0.9469 0.0112
-8.750 -0.5619 0.02850 0.02270 -0.0825 0.9401 0.0118
-8.500 -0.5424 0.02628 0.02008 -0.0822 0.9332 0.0126
-8.250 -0.5181 0.02550 0.01917 -0.0823 0.9280 0.0134
-8.000 -0.4955 0.02427 0.01771 -0.0821 0.9213 0.0144
-7.750 -0.4730 0.02260 0.01569 -0.0816 0.9158 0.0154
-7.500 -0.4494 0.02133 0.01421 -0.0813 0.9104 0.0166
-7.250 -0.4245 0.02060 0.01337 -0.0811 0.9046 0.0181
-7.000 -0.3999 0.01958 0.01210 -0.0807 0.8999 0.0207
-6.750 -0.3738 0.01913 0.01160 -0.0807 0.8947 0.0234
-6.500 -0.3475 0.01865 0.01098 -0.0806 0.8893 0.0275
-6.250 -0.3210 0.01841 0.01064 -0.0805 0.8849 0.0316
-6.000 -0.2943 0.01804 0.01017 -0.0806 0.8799 0.0359
-5.750 -0.2671 0.01785 0.00988 -0.0807 0.8749 0.0407
-5.500 -0.2409 0.01723 0.00913 -0.0805 0.8705 0.0439
-5.250 -0.2144 0.01671 0.00858 -0.0805 0.8660 0.0472
-5.000 -0.1873 0.01626 0.00804 -0.0805 0.8608 0.0507
-4.750 -0.1602 0.01584 0.00748 -0.0804 0.8564 0.0534
-4.500 -0.1337 0.01529 0.00692 -0.0804 0.8523 0.0575
-4.250 -0.1060 0.01493 0.00651 -0.0806 0.8470 0.0619
-4.000 -0.0784 0.01462 0.00608 -0.0806 0.8424 0.0662
-3.750 -0.0512 0.01423 0.00569 -0.0806 0.8387 0.0737
-3.500 -0.0230 0.01393 0.00538 -0.0809 0.8334 0.0835
-3.250 0.0049 0.01362 0.00508 -0.0811 0.8287 0.0991
-3.000 0.0325 0.01325 0.00480 -0.0813 0.8248 0.1330
-2.750 0.0600 0.01275 0.00458 -0.0817 0.8201 0.2070
-2.500 0.0868 0.01214 0.00448 -0.0820 0.8151 0.3438
-2.250 0.1145 0.01192 0.00438 -0.0821 0.8109 0.4136
-2.000 0.1423 0.01173 0.00429 -0.0822 0.8068 0.4578
-1.750 0.1700 0.01153 0.00423 -0.0824 0.8014 0.5036
-1.500 0.1969 0.01125 0.00418 -0.0822 0.7970 0.5693
-1.250 0.2215 0.01084 0.00418 -0.0814 0.7932 0.6766
-0.750 0.2690 0.01030 0.00426 -0.0781 0.7828 0.9194
-0.500 0.3063 0.01026 0.00414 -0.0800 0.7791 0.9595
-0.250 0.3444 0.01029 0.00411 -0.0824 0.7734 0.9893
0.000 0.3775 0.01028 0.00403 -0.0837 0.7682 1.0000
0.250 0.4043 0.01031 0.00395 -0.0836 0.7637 1.0000
0.500 0.4313 0.01037 0.00398 -0.0836 0.7573 1.0000
0.750 0.4586 0.01041 0.00395 -0.0836 0.7522 1.0000
1.000 0.4861 0.01047 0.00396 -0.0836 0.7470 1.0000
1.250 0.5136 0.01054 0.00401 -0.0837 0.7409 1.0000
1.500 0.5414 0.01059 0.00400 -0.0838 0.7359 1.0000
1.750 0.5690 0.01068 0.00408 -0.0839 0.7294 1.0000
2.000 0.5968 0.01074 0.00412 -0.0840 0.7231 1.0000
2.250 0.6245 0.01082 0.00419 -0.0840 0.7163 1.0000
2.500 0.6522 0.01089 0.00425 -0.0841 0.7088 1.0000
2.750 0.6799 0.01097 0.00433 -0.0842 0.7013 1.0000
3.000 0.7076 0.01104 0.00440 -0.0842 0.6930 1.0000
3.250 0.7351 0.01113 0.00451 -0.0842 0.6834 1.0000
3.500 0.7626 0.01121 0.00458 -0.0842 0.6741 1.0000
3.750 0.7900 0.01130 0.00469 -0.0841 0.6633 1.0000
4.000 0.8171 0.01140 0.00481 -0.0841 0.6512 1.0000
4.250 0.8441 0.01151 0.00493 -0.0840 0.6383 1.0000
4.500 0.8709 0.01163 0.00508 -0.0838 0.6240 1.0000
4.750 0.8973 0.01177 0.00521 -0.0836 0.6073 1.0000
5.000 0.9232 0.01194 0.00536 -0.0833 0.5884 1.0000
5.250 0.9487 0.01214 0.00555 -0.0829 0.5650 1.0000
5.500 0.9730 0.01241 0.00576 -0.0823 0.5355 1.0000
5.750 0.9960 0.01278 0.00601 -0.0815 0.4999 1.0000
6.000 1.0173 0.01327 0.00633 -0.0804 0.4567 1.0000
6.250 1.0357 0.01396 0.00679 -0.0790 0.4030 1.0000
6.500 1.0508 0.01489 0.00739 -0.0771 0.3412 1.0000
6.750 1.0648 0.01588 0.00809 -0.0751 0.2834 1.0000
7.000 1.0791 0.01685 0.00882 -0.0733 0.2355 1.0000
7.250 1.0938 0.01777 0.00955 -0.0715 0.1954 1.0000
7.500 1.1084 0.01867 0.01032 -0.0697 0.1623 1.0000
7.750 1.1220 0.01958 0.01110 -0.0677 0.1329 1.0000
8.000 1.1346 0.02051 0.01192 -0.0656 0.1085 1.0000
8.250 1.1461 0.02140 0.01275 -0.0633 0.0899 1.0000
8.500 1.1567 0.02231 0.01364 -0.0609 0.0761 1.0000
8.750 1.1677 0.02328 0.01462 -0.0586 0.0652 1.0000
9.000 1.1787 0.02431 0.01565 -0.0565 0.0568 1.0000
9.250 1.1890 0.02543 0.01678 -0.0545 0.0499 1.0000
9.500 1.2011 0.02647 0.01789 -0.0527 0.0445 1.0000
9.750 1.2109 0.02771 0.01913 -0.0509 0.0397 1.0000
10.000 1.2226 0.02883 0.02035 -0.0492 0.0360 1.0000
10.250 1.2332 0.03006 0.02166 -0.0476 0.0327 1.0000
10.500 1.2412 0.03154 0.02319 -0.0459 0.0300 1.0000
10.750 1.2516 0.03285 0.02463 -0.0444 0.0277 1.0000
11.000 1.2605 0.03432 0.02619 -0.0428 0.0258 1.0000
11.250 1.2660 0.03610 0.02802 -0.0412 0.0240 1.0000
11.500 1.2727 0.03783 0.02987 -0.0396 0.0225 1.0000
11.750 1.2804 0.03950 0.03167 -0.0382 0.0209 1.0000
12.000 1.2874 0.04125 0.03352 -0.0370 0.0195 1.0000
12.250 1.2913 0.04332 0.03567 -0.0357 0.0184 1.0000
12.500 1.2943 0.04555 0.03801 -0.0343 0.0176 1.0000
12.750 1.2988 0.04769 0.04031 -0.0331 0.0168 1.0000
13.000 1.3025 0.04994 0.04271 -0.0319 0.0160 1.0000
13.250 1.3055 0.05229 0.04519 -0.0309 0.0154 1.0000
13.500 1.3079 0.05474 0.04777 -0.0300 0.0148 1.0000
13.750 1.3094 0.05733 0.05047 -0.0293 0.0144 1.0000
14.000 1.3092 0.06018 0.05341 -0.0287 0.0139 1.0000
14.250 1.3081 0.06324 0.05660 -0.0281 0.0135 1.0000
14.500 1.3084 0.06627 0.05984 -0.0277 0.0130 1.0000
14.750 1.3076 0.06952 0.06331 -0.0275 0.0126 1.0000
15.000 1.3054 0.07300 0.06697 -0.0275 0.0121 1.0000
15.250 1.3022 0.07673 0.07087 -0.0278 0.0118 1.0000
15.500 1.2977 0.08074 0.07506 -0.0283 0.0115 1.0000
15.750 1.2923 0.08502 0.07951 -0.0291 0.0113 1.0000
16.000 1.2859 0.08957 0.08423 -0.0302 0.0111 1.0000
16.250 1.2786 0.09439 0.08920 -0.0316 0.0110 1.0000
16.500 1.2705 0.09950 0.09447 -0.0334 0.0108 1.0000
16.750 1.2615 0.10494 0.10007 -0.0355 0.0107 1.0000
17.000 1.2516 0.11074 0.10603 -0.0380 0.0106 1.0000
17.250 1.2406 0.11690 0.11235 -0.0409 0.0105 1.0000
17.500 1.2287 0.12348 0.11910 -0.0442 0.0104 1.0000
17.750 1.2156 0.13061 0.12640 -0.0481 0.0104 1.0000
18.000 1.2014 0.13834 0.13431 -0.0526 0.0104 1.0000
18.250 1.1851 0.14708 0.14324 -0.0580 0.0104 1.0000
18.500 1.1649 0.15738 0.15376 -0.0646 0.0104 1.0000
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