SG6050 (sg6050-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6050 (sg6050-il) Reynolds number: 100,000 Max Cl/Cd: 50.03 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6050-il-100000.txt Download as CSV file: xf-sg6050-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SG6050
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.4247 0.13166 0.12669 -0.0436 1.0000 0.1297
-12.000 -0.4543 0.11017 0.10525 -0.0527 1.0000 0.0879
-11.750 -0.6008 0.07273 0.06770 -0.0772 1.0000 0.0643
-11.500 -0.6270 0.06679 0.06170 -0.0803 1.0000 0.0638
-11.250 -0.6558 0.06269 0.05755 -0.0802 1.0000 0.0634
-11.000 -0.6873 0.06059 0.05545 -0.0760 1.0000 0.0630
-10.750 -0.7191 0.05909 0.05394 -0.0705 1.0000 0.0627
-10.500 -0.7500 0.05753 0.05232 -0.0649 1.0000 0.0625
-10.250 -0.7780 0.05536 0.04997 -0.0600 1.0000 0.0626
-10.000 -0.8022 0.05257 0.04684 -0.0557 1.0000 0.0633
-9.500 -0.8093 0.04848 0.04254 -0.0504 1.0000 0.0681
-9.250 -0.8092 0.04651 0.04034 -0.0481 1.0000 0.0718
-9.000 -0.8001 0.04299 0.03626 -0.0482 0.9973 0.0776
-8.750 -0.7704 0.04164 0.03451 -0.0505 0.9924 0.0872
-8.500 -0.7399 0.04021 0.03324 -0.0528 0.9874 0.0965
-8.250 -0.7087 0.03812 0.03082 -0.0554 0.9831 0.1059
-8.000 -0.6818 0.03681 0.02904 -0.0565 0.9770 0.1143
-7.750 -0.6486 0.03491 0.02712 -0.0589 0.9726 0.1217
-7.500 -0.6172 0.03367 0.02541 -0.0605 0.9675 0.1288
-7.250 -0.5864 0.03204 0.02374 -0.0621 0.9622 0.1349
-7.000 -0.5484 0.03097 0.02240 -0.0647 0.9581 0.1425
-6.750 -0.5190 0.02976 0.02108 -0.0656 0.9525 0.1481
-6.500 -0.4862 0.02889 0.02015 -0.0671 0.9470 0.1555
-6.250 -0.4465 0.02783 0.01897 -0.0698 0.9433 0.1632
-6.000 -0.4183 0.02718 0.01833 -0.0704 0.9373 0.1721
-5.750 -0.3864 0.02639 0.01759 -0.0716 0.9317 0.1825
-5.500 -0.3470 0.02555 0.01683 -0.0743 0.9279 0.1985
-5.250 -0.3190 0.02496 0.01635 -0.0749 0.9219 0.2217
-5.000 -0.2900 0.02425 0.01604 -0.0758 0.9158 0.2688
-4.750 -0.2508 0.02431 0.01642 -0.0781 0.9115 0.3609
-4.500 -0.2280 0.02477 0.01681 -0.0774 0.9040 0.4015
-4.250 -0.1958 0.02496 0.01691 -0.0784 0.8980 0.4328
-4.000 -0.1535 0.02490 0.01687 -0.0811 0.8945 0.4595
-3.750 -0.1351 0.02515 0.01711 -0.0797 0.8862 0.4773
-3.500 -0.0993 0.02512 0.01701 -0.0813 0.8809 0.4985
-3.250 -0.0563 0.02491 0.01678 -0.0839 0.8776 0.5197
-3.000 -0.0400 0.02522 0.01710 -0.0822 0.8684 0.5358
-2.750 -0.0049 0.02509 0.01704 -0.0834 0.8634 0.5573
-2.500 0.0359 0.02485 0.01681 -0.0853 0.8603 0.5816
-2.250 0.0485 0.02526 0.01726 -0.0831 0.8498 0.5962
-2.000 0.0863 0.02498 0.01697 -0.0847 0.8456 0.6121
-1.750 0.1107 0.02512 0.01710 -0.0844 0.8381 0.6249
-1.500 0.1397 0.02509 0.01707 -0.0848 0.8313 0.6392
-1.250 0.1786 0.02472 0.01670 -0.0864 0.8277 0.6560
-1.000 0.1946 0.02515 0.01719 -0.0849 0.8176 0.6720
-0.750 0.2280 0.02485 0.01699 -0.0855 0.8127 0.6929
-0.500 0.2544 0.02484 0.01708 -0.0850 0.8064 0.7192
-0.250 0.2748 0.02495 0.01737 -0.0835 0.7980 0.7536
0.000 0.3045 0.02453 0.01718 -0.0822 0.7943 0.8107
0.250 0.3143 0.02513 0.01798 -0.0784 0.7836 0.8976
0.500 0.3966 0.02472 0.01751 -0.0880 0.7805 0.9861
0.750 0.4548 0.02418 0.01679 -0.0938 0.7772 1.0000
1.000 0.4565 0.02498 0.01750 -0.0903 0.7650 1.0000
1.250 0.4921 0.02461 0.01700 -0.0912 0.7610 1.0000
1.500 0.5010 0.02543 0.01777 -0.0887 0.7494 1.0000
1.750 0.5368 0.02507 0.01732 -0.0895 0.7451 1.0000
2.000 0.5496 0.02585 0.01808 -0.0876 0.7340 1.0000
2.250 0.5845 0.02553 0.01768 -0.0883 0.7294 1.0000
2.500 0.6007 0.02621 0.01835 -0.0868 0.7190 1.0000
2.750 0.6344 0.02591 0.01801 -0.0872 0.7136 1.0000
3.000 0.6544 0.02642 0.01851 -0.0862 0.7042 1.0000
3.250 0.6861 0.02620 0.01827 -0.0864 0.6979 1.0000
3.500 0.7208 0.02584 0.01787 -0.0869 0.6930 1.0000
3.750 0.7393 0.02637 0.01843 -0.0857 0.6821 1.0000
4.000 0.7784 0.02571 0.01773 -0.0866 0.6783 1.0000
4.250 0.7935 0.02646 0.01854 -0.0850 0.6663 1.0000
4.500 0.8329 0.02576 0.01781 -0.0860 0.6623 1.0000
4.750 0.8486 0.02648 0.01861 -0.0844 0.6504 1.0000
5.000 0.8888 0.02572 0.01781 -0.0855 0.6462 1.0000
5.250 0.9048 0.02641 0.01858 -0.0839 0.6342 1.0000
5.500 0.9349 0.02626 0.01847 -0.0839 0.6266 1.0000
5.750 0.9625 0.02621 0.01846 -0.0836 0.6175 1.0000
6.000 0.9871 0.02637 0.01868 -0.0829 0.6077 1.0000
6.250 1.0227 0.02580 0.01810 -0.0834 0.6000 1.0000
6.500 1.0436 0.02613 0.01852 -0.0823 0.5884 1.0000
6.750 1.0795 0.02559 0.01796 -0.0829 0.5802 1.0000
7.000 1.1045 0.02563 0.01807 -0.0822 0.5687 1.0000
7.250 1.1271 0.02584 0.01835 -0.0812 0.5568 1.0000
7.500 1.1565 0.02567 0.01821 -0.0810 0.5459 1.0000
7.750 1.1898 0.02530 0.01780 -0.0813 0.5348 1.0000
8.000 1.2104 0.02554 0.01814 -0.0800 0.5211 1.0000
8.250 1.2326 0.02573 0.01840 -0.0789 0.5074 1.0000
8.500 1.2557 0.02588 0.01859 -0.0779 0.4935 1.0000
8.750 1.2786 0.02602 0.01876 -0.0769 0.4790 1.0000
9.000 1.3002 0.02619 0.01896 -0.0757 0.4638 1.0000
9.250 1.3200 0.02643 0.01924 -0.0742 0.4479 1.0000
9.500 1.3379 0.02674 0.01957 -0.0725 0.4314 1.0000
9.750 1.3537 0.02713 0.01999 -0.0705 0.4145 1.0000
10.000 1.3672 0.02760 0.02047 -0.0682 0.3971 1.0000
10.250 1.3780 0.02813 0.02104 -0.0656 0.3795 1.0000
10.500 1.3859 0.02876 0.02165 -0.0625 0.3618 1.0000
10.750 1.3893 0.02948 0.02234 -0.0588 0.3444 1.0000
11.000 1.3883 0.03047 0.02334 -0.0548 0.3269 1.0000
11.250 1.3851 0.03172 0.02462 -0.0510 0.3089 1.0000
11.500 1.3818 0.03318 0.02609 -0.0476 0.2905 1.0000
11.750 1.3784 0.03482 0.02773 -0.0445 0.2722 1.0000
12.000 1.3750 0.03664 0.02950 -0.0417 0.2541 1.0000
12.250 1.3715 0.03865 0.03141 -0.0392 0.2363 1.0000
12.500 1.3663 0.04095 0.03368 -0.0369 0.2189 1.0000
12.750 1.3607 0.04343 0.03614 -0.0349 0.2021 1.0000
13.000 1.3554 0.04603 0.03870 -0.0330 0.1863 1.0000
13.250 1.3500 0.04874 0.04137 -0.0313 0.1714 1.0000
13.500 1.3449 0.05156 0.04413 -0.0299 0.1576 1.0000
13.750 1.3397 0.05444 0.04695 -0.0285 0.1449 1.0000
14.000 1.3350 0.05737 0.04979 -0.0274 0.1331 1.0000
14.250 1.3285 0.06064 0.05312 -0.0266 0.1225 1.0000
14.500 1.3227 0.06399 0.05653 -0.0259 0.1124 1.0000
14.750 1.3187 0.06721 0.05974 -0.0253 0.1034 1.0000
15.000 1.3180 0.07003 0.06240 -0.0246 0.0947 1.0000
15.250 1.3115 0.07386 0.06646 -0.0245 0.0877 1.0000
15.500 1.3117 0.07677 0.06931 -0.0240 0.0808 1.0000
15.750 1.3087 0.08024 0.07288 -0.0239 0.0749 1.0000
16.000 1.3107 0.08310 0.07574 -0.0233 0.0694 1.0000
16.250 1.3082 0.08662 0.07939 -0.0234 0.0649 1.0000
16.500 1.3150 0.08887 0.08157 -0.0227 0.0604 1.0000
16.750 1.3091 0.09310 0.08607 -0.0232 0.0576 1.0000
17.000 1.3110 0.09619 0.08925 -0.0232 0.0548 1.0000
17.250 1.3257 0.09774 0.09069 -0.0220 0.0519 1.0000
17.500 1.3140 0.10291 0.09620 -0.0233 0.0509 1.0000
17.750 1.3021 0.10828 0.10187 -0.0249 0.0498 1.0000
18.000 1.2896 0.11389 0.10774 -0.0269 0.0489 1.0000
18.250 1.2764 0.11979 0.11387 -0.0294 0.0481 1.0000
18.500 1.2615 0.12620 0.12051 -0.0324 0.0475 1.0000
18.750 1.2406 0.13403 0.12860 -0.0367 0.0473 1.0000
19.000 1.1976 0.14717 0.14213 -0.0451 0.0487 1.0000
19.250 1.1502 0.16288 0.15813 -0.0556 0.0505 1.0000
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