S9000 (9%) (s9000-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9000 (9%) (s9000-il) Reynolds number: 1,000,000 Max Cl/Cd: 97.27 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9000-il-1000000-n5.txt Download as CSV file: xf-s9000-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9000 (9%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4551 0.08397 0.08235 -0.0272 1.0000 0.0042
-8.000 -0.5522 0.02681 0.02412 -0.0653 0.9892 0.0029
-7.750 -0.5302 0.02144 0.01810 -0.0678 0.9860 0.0028
-7.500 -0.5018 0.01857 0.01482 -0.0695 0.9842 0.0028
-7.250 -0.4765 0.01654 0.01247 -0.0699 0.9808 0.0028
-7.000 -0.4496 0.01508 0.01077 -0.0703 0.9770 0.0028
-6.750 -0.4199 0.01382 0.00928 -0.0711 0.9742 0.0028
-6.500 -0.3887 0.01275 0.00803 -0.0721 0.9717 0.0028
-6.250 -0.3621 0.01194 0.00709 -0.0720 0.9658 0.0028
-6.000 -0.3327 0.01118 0.00622 -0.0725 0.9595 0.0029
-5.750 -0.3027 0.01052 0.00546 -0.0730 0.9527 0.0029
-5.500 -0.2715 0.00994 0.00478 -0.0738 0.9450 0.0029
-5.250 -0.2406 0.00946 0.00422 -0.0745 0.9357 0.0030
-5.000 -0.2101 0.00904 0.00370 -0.0750 0.9243 0.0030
-4.750 -0.1811 0.00871 0.00328 -0.0752 0.9093 0.0031
-4.500 -0.1535 0.00837 0.00282 -0.0750 0.8910 0.0033
-4.250 -0.1265 0.00814 0.00247 -0.0747 0.8721 0.0039
-4.000 -0.0996 0.00798 0.00221 -0.0744 0.8536 0.0047
-3.750 -0.0728 0.00781 0.00198 -0.0741 0.8359 0.0074
-3.500 -0.0460 0.00765 0.00179 -0.0738 0.8196 0.0139
-3.250 -0.0190 0.00753 0.00163 -0.0736 0.8037 0.0213
-3.000 0.0079 0.00738 0.00148 -0.0733 0.7877 0.0351
-2.750 0.0346 0.00716 0.00134 -0.0731 0.7694 0.0695
-2.500 0.0612 0.00699 0.00121 -0.0729 0.7488 0.1056
-2.250 0.0881 0.00686 0.00111 -0.0727 0.7297 0.1394
-1.750 0.1423 0.00661 0.00096 -0.0725 0.6939 0.2186
-1.500 0.1692 0.00646 0.00090 -0.0724 0.6748 0.2736
-1.250 0.1963 0.00637 0.00086 -0.0723 0.6552 0.3205
-1.000 0.2233 0.00631 0.00083 -0.0721 0.6321 0.3651
-0.750 0.2502 0.00622 0.00082 -0.0720 0.6087 0.4236
-0.500 0.2773 0.00616 0.00081 -0.0719 0.5882 0.4727
-0.250 0.3044 0.00606 0.00082 -0.0718 0.5698 0.5343
0.000 0.3316 0.00598 0.00084 -0.0717 0.5506 0.5936
0.250 0.3586 0.00594 0.00088 -0.0716 0.5309 0.6512
0.500 0.3856 0.00597 0.00093 -0.0714 0.5090 0.6927
0.750 0.4122 0.00606 0.00099 -0.0711 0.4819 0.7265
1.000 0.4390 0.00616 0.00106 -0.0708 0.4573 0.7519
1.250 0.4661 0.00625 0.00113 -0.0706 0.4368 0.7706
1.500 0.4930 0.00634 0.00120 -0.0704 0.4184 0.7904
1.750 0.5197 0.00645 0.00128 -0.0701 0.3995 0.8088
2.000 0.5464 0.00657 0.00137 -0.0698 0.3788 0.8260
2.250 0.5729 0.00669 0.00146 -0.0695 0.3610 0.8425
2.500 0.5989 0.00683 0.00156 -0.0691 0.3393 0.8594
2.750 0.6241 0.00702 0.00168 -0.0686 0.3116 0.8780
3.000 0.6491 0.00717 0.00181 -0.0679 0.2904 0.8973
3.250 0.6732 0.00729 0.00192 -0.0671 0.2744 0.9192
3.500 0.6960 0.00741 0.00203 -0.0659 0.2561 0.9487
3.750 0.7271 0.00756 0.00214 -0.0666 0.2377 1.0000
4.000 0.7541 0.00776 0.00229 -0.0665 0.2229 1.0000
4.500 0.8062 0.00836 0.00266 -0.0660 0.1762 1.0000
4.750 0.8325 0.00863 0.00285 -0.0658 0.1593 1.0000
5.000 0.8589 0.00888 0.00305 -0.0657 0.1462 1.0000
5.500 0.9115 0.00938 0.00347 -0.0652 0.1229 1.0000
5.750 0.9377 0.00964 0.00371 -0.0650 0.1120 1.0000
6.000 0.9633 0.00995 0.00396 -0.0647 0.0990 1.0000
6.250 0.9889 0.01027 0.00423 -0.0644 0.0870 1.0000
6.500 1.0145 0.01058 0.00451 -0.0641 0.0779 1.0000
6.750 1.0394 0.01095 0.00484 -0.0637 0.0661 1.0000
7.000 1.0641 0.01134 0.00518 -0.0633 0.0545 1.0000
7.250 1.0887 0.01175 0.00553 -0.0629 0.0449 1.0000
7.500 1.1136 0.01209 0.00587 -0.0625 0.0397 1.0000
7.750 1.1382 0.01247 0.00624 -0.0621 0.0344 1.0000
8.000 1.1627 0.01284 0.00662 -0.0616 0.0304 1.0000
8.250 1.1867 0.01326 0.00704 -0.0611 0.0257 1.0000
8.500 1.2105 0.01368 0.00746 -0.0606 0.0211 1.0000
8.750 1.2333 0.01420 0.00795 -0.0599 0.0157 1.0000
9.000 1.2559 0.01473 0.00847 -0.0592 0.0119 1.0000
9.250 1.2782 0.01528 0.00902 -0.0585 0.0093 1.0000
9.500 1.3009 0.01576 0.00954 -0.0578 0.0079 1.0000
9.750 1.3227 0.01630 0.01012 -0.0571 0.0066 1.0000
10.000 1.3444 0.01684 0.01070 -0.0563 0.0058 1.0000
10.250 1.3660 0.01737 0.01128 -0.0555 0.0051 1.0000
10.500 1.3867 0.01795 0.01191 -0.0545 0.0045 1.0000
10.750 1.4064 0.01859 0.01260 -0.0535 0.0039 1.0000
11.000 1.4265 0.01917 0.01324 -0.0525 0.0035 1.0000
11.250 1.4455 0.01980 0.01393 -0.0514 0.0030 1.0000
11.500 1.4630 0.02053 0.01473 -0.0501 0.0025 1.0000
11.750 1.4798 0.02126 0.01553 -0.0487 0.0021 1.0000
12.000 1.4956 0.02202 0.01636 -0.0472 0.0017 1.0000
12.250 1.5081 0.02285 0.01726 -0.0451 0.0014 1.0000
12.500 1.5174 0.02375 0.01823 -0.0426 0.0011 1.0000
12.750 1.5267 0.02462 0.01919 -0.0401 0.0011 1.0000
13.000 1.5336 0.02567 0.02034 -0.0376 0.0009 1.0000
13.250 1.5403 0.02677 0.02153 -0.0352 0.0008 1.0000
13.500 1.5450 0.02806 0.02292 -0.0328 0.0008 1.0000
13.750 1.5482 0.02952 0.02448 -0.0306 0.0007 1.0000
14.000 1.5505 0.03114 0.02623 -0.0287 0.0006 1.0000
14.250 1.5505 0.03308 0.02829 -0.0269 0.0006 1.0000
14.500 1.5504 0.03517 0.03051 -0.0255 0.0006 1.0000
14.750 1.5436 0.03810 0.03359 -0.0244 0.0005 1.0000
15.000 1.5425 0.04067 0.03628 -0.0238 0.0005 1.0000
15.250 1.5339 0.04432 0.04008 -0.0238 0.0005 1.0000
15.500 1.5231 0.04859 0.04451 -0.0245 0.0005 1.0000
15.750 1.5144 0.05291 0.04897 -0.0257 0.0005 1.0000
16.000 1.5027 0.05801 0.05422 -0.0275 0.0005 1.0000
16.250 1.4886 0.06385 0.06022 -0.0301 0.0005 1.0000
16.500 1.4723 0.07043 0.06695 -0.0334 0.0005 1.0000
16.750 1.4516 0.07822 0.07490 -0.0375 0.0005 1.0000
17.000 1.4319 0.08618 0.08301 -0.0418 0.0005 1.0000
17.250 1.4020 0.09660 0.09361 -0.0477 0.0005 1.0000
17.500 1.3775 0.10621 0.10337 -0.0531 0.0005 1.0000
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Polar data table (+)
Polar graphs
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