S9037 (9%) (s9037-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S9037 (9%) (s9037-il) Reynolds number: 200,000 Max Cl/Cd: 78.14 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9037-il-200000.txt Download as CSV file: xf-s9037-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S9037 (9%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3616 0.08900 0.08585 -0.0375 1.0000 0.0381
-7.500 -0.3716 0.08676 0.08368 -0.0374 1.0000 0.0382
-7.250 -0.3815 0.08449 0.08146 -0.0371 1.0000 0.0382
-7.000 -0.3949 0.08068 0.07771 -0.0365 1.0000 0.0385
-6.750 -0.4031 0.07764 0.07475 -0.0317 1.0000 0.0393
-6.500 -0.4082 0.07569 0.07283 -0.0290 1.0000 0.0399
-6.250 -0.3942 0.07260 0.06975 -0.0306 0.9975 0.0411
-6.000 -0.3653 0.06787 0.06497 -0.0376 0.9924 0.0433
-5.750 -0.3319 0.06202 0.05901 -0.0474 0.9861 0.0464
-5.500 -0.2883 0.05243 0.04881 -0.0638 0.9774 0.0509
-5.250 -0.2632 0.04863 0.04512 -0.0658 0.9734 0.0526
-5.000 -0.2295 0.04531 0.04173 -0.0699 0.9700 0.0559
-4.750 -0.1963 0.04005 0.03582 -0.0754 0.9613 0.0646
-4.500 -0.1626 0.03678 0.03260 -0.0784 0.9580 0.0675
-4.250 -0.1300 0.03373 0.02902 -0.0812 0.9510 0.0784
-4.000 -0.0877 0.02413 0.01795 -0.0812 0.9468 0.0284
-3.750 -0.0477 0.02095 0.01439 -0.0837 0.9441 0.0267
-3.500 -0.0117 0.01883 0.01188 -0.0849 0.9391 0.0264
-3.250 0.0236 0.01734 0.01013 -0.0858 0.9332 0.0274
-3.000 0.0615 0.01566 0.00840 -0.0876 0.9296 0.0316
-2.750 0.0919 0.01497 0.00765 -0.0876 0.9217 0.0386
-2.500 0.1253 0.01355 0.00632 -0.0884 0.9162 0.0673
-2.250 0.1525 0.01240 0.00572 -0.0884 0.9078 0.1900
-2.000 0.1817 0.01145 0.00544 -0.0888 0.9012 0.3741
-1.750 0.2031 0.01064 0.00534 -0.0873 0.8914 0.5764
-1.500 0.2232 0.00976 0.00526 -0.0840 0.8851 0.8407
-1.250 0.2932 0.00938 0.00479 -0.0918 0.8800 1.0000
-1.000 0.3192 0.00929 0.00452 -0.0910 0.8712 1.0000
-0.750 0.3421 0.00929 0.00437 -0.0897 0.8593 1.0000
-0.500 0.3661 0.00929 0.00422 -0.0886 0.8481 1.0000
-0.250 0.3910 0.00928 0.00407 -0.0876 0.8373 1.0000
0.000 0.4165 0.00926 0.00392 -0.0868 0.8268 1.0000
0.250 0.4418 0.00925 0.00378 -0.0859 0.8152 1.0000
0.500 0.4669 0.00927 0.00369 -0.0850 0.8024 1.0000
0.750 0.4922 0.00930 0.00362 -0.0842 0.7895 1.0000
1.000 0.5178 0.00934 0.00357 -0.0834 0.7763 1.0000
1.250 0.5435 0.00938 0.00352 -0.0827 0.7629 1.0000
1.500 0.5694 0.00944 0.00350 -0.0821 0.7492 1.0000
1.750 0.5953 0.00952 0.00348 -0.0814 0.7350 1.0000
2.000 0.6212 0.00960 0.00350 -0.0808 0.7203 1.0000
2.250 0.6470 0.00970 0.00351 -0.0801 0.7047 1.0000
2.500 0.6728 0.00981 0.00353 -0.0795 0.6885 1.0000
2.750 0.6984 0.00993 0.00357 -0.0788 0.6716 1.0000
3.000 0.7238 0.01007 0.00366 -0.0782 0.6535 1.0000
3.250 0.7493 0.01023 0.00377 -0.0776 0.6357 1.0000
3.500 0.7748 0.01040 0.00387 -0.0769 0.6179 1.0000
3.750 0.7999 0.01059 0.00400 -0.0763 0.5986 1.0000
4.000 0.8248 0.01079 0.00413 -0.0756 0.5778 1.0000
4.250 0.8496 0.01102 0.00431 -0.0749 0.5573 1.0000
4.500 0.8741 0.01126 0.00450 -0.0742 0.5359 1.0000
4.750 0.8985 0.01154 0.00471 -0.0735 0.5155 1.0000
5.000 0.9228 0.01181 0.00495 -0.0728 0.4937 1.0000
5.250 0.9467 0.01213 0.00523 -0.0721 0.4727 1.0000
5.500 0.9704 0.01245 0.00552 -0.0714 0.4504 1.0000
5.750 0.9936 0.01282 0.00583 -0.0706 0.4280 1.0000
6.000 1.0164 0.01321 0.00615 -0.0697 0.4045 1.0000
6.250 1.0391 0.01360 0.00654 -0.0689 0.3807 1.0000
6.500 1.0613 0.01404 0.00693 -0.0680 0.3580 1.0000
6.750 1.0832 0.01450 0.00736 -0.0670 0.3351 1.0000
7.000 1.1048 0.01499 0.00782 -0.0661 0.3118 1.0000
7.250 1.1255 0.01554 0.00833 -0.0650 0.2889 1.0000
7.500 1.1461 0.01610 0.00887 -0.0640 0.2657 1.0000
7.750 1.1658 0.01671 0.00944 -0.0629 0.2424 1.0000
8.000 1.1843 0.01741 0.01006 -0.0616 0.2201 1.0000
8.250 1.2036 0.01806 0.01071 -0.0604 0.1979 1.0000
8.500 1.2205 0.01888 0.01147 -0.0590 0.1788 1.0000
8.750 1.2383 0.01962 0.01225 -0.0577 0.1595 1.0000
9.000 1.2544 0.02048 0.01309 -0.0561 0.1424 1.0000
9.250 1.2688 0.02144 0.01401 -0.0544 0.1270 1.0000
9.500 1.2815 0.02250 0.01504 -0.0524 0.1126 1.0000
9.750 1.2930 0.02355 0.01610 -0.0503 0.0998 1.0000
10.000 1.3032 0.02458 0.01718 -0.0480 0.0886 1.0000
10.250 1.3123 0.02569 0.01836 -0.0456 0.0786 1.0000
10.500 1.3193 0.02698 0.01971 -0.0431 0.0698 1.0000
10.750 1.3236 0.02844 0.02113 -0.0407 0.0617 1.0000
11.000 1.3341 0.02940 0.02222 -0.0391 0.0534 1.0000
11.250 1.3403 0.03082 0.02374 -0.0372 0.0463 1.0000
11.500 1.3410 0.03273 0.02565 -0.0351 0.0408 1.0000
11.750 1.3467 0.03438 0.02747 -0.0335 0.0346 1.0000
12.000 1.3400 0.03723 0.03034 -0.0315 0.0299 1.0000
12.250 1.3408 0.03954 0.03282 -0.0301 0.0253 1.0000
12.500 1.3336 0.04277 0.03610 -0.0288 0.0231 1.0000
12.750 1.3287 0.04611 0.03960 -0.0276 0.0212 1.0000
13.000 1.3274 0.04915 0.04283 -0.0269 0.0195 1.0000
13.250 1.3258 0.05229 0.04611 -0.0264 0.0185 1.0000
13.500 1.3230 0.05562 0.04956 -0.0263 0.0175 1.0000
13.750 1.3183 0.05933 0.05339 -0.0265 0.0166 1.0000
14.000 1.3114 0.06370 0.05791 -0.0264 0.0159 1.0000
14.250 1.3042 0.06815 0.06258 -0.0271 0.0154 1.0000
14.500 1.2982 0.07250 0.06715 -0.0281 0.0151 1.0000
14.750 1.2906 0.07721 0.07209 -0.0299 0.0145 1.0000
15.000 1.2812 0.08252 0.07761 -0.0318 0.0143 1.0000
15.250 1.2708 0.08817 0.08348 -0.0342 0.0141 1.0000
15.500 1.2587 0.09439 0.08991 -0.0371 0.0139 1.0000
15.750 1.2450 0.10121 0.09693 -0.0405 0.0139 1.0000
16.000 1.2301 0.10854 0.10448 -0.0445 0.0139 1.0000
16.250 1.2141 0.11642 0.11256 -0.0491 0.0139 1.0000
16.500 1.1971 0.12492 0.12125 -0.0542 0.0140 1.0000
16.750 1.1792 0.13404 0.13055 -0.0600 0.0142 1.0000
17.000 1.1600 0.14394 0.14061 -0.0663 0.0144 1.0000
17.250 1.1393 0.15483 0.15164 -0.0734 0.0148 1.0000
17.500 1.1161 0.16677 0.16364 -0.0808 0.0155 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S9037 (9%) (s9037-il)