S4180-098-84 (s4180-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4180-098-84 (s4180-il) Reynolds number: 500,000 Max Cl/Cd: 110.53 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4180-il-500000.txt Download as CSV file: xf-s4180-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S4180-098-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2883 0.08862 0.08646 -0.0279 1.0000 0.0239
-8.000 -0.2844 0.08565 0.08352 -0.0292 1.0000 0.0244
-7.500 -0.2817 0.07568 0.07365 -0.0422 0.9791 0.0261
-7.250 -0.2614 0.07102 0.06898 -0.0467 0.9640 0.0266
-7.000 -0.2358 0.06799 0.06592 -0.0511 0.9452 0.0272
-6.750 -0.2199 0.06489 0.06275 -0.0547 0.9199 0.0277
-6.500 -0.2095 0.06175 0.05951 -0.0577 0.8971 0.0286
-6.250 -0.1983 0.05761 0.05528 -0.0622 0.8774 0.0298
-6.000 -0.1838 0.04513 0.04246 -0.0769 0.8587 0.0321
-5.750 -0.1665 0.04340 0.04066 -0.0772 0.8458 0.0325
-5.500 -0.1470 0.04215 0.03933 -0.0774 0.8330 0.0333
-5.250 -0.1251 0.03948 0.03653 -0.0791 0.8204 0.0346
-5.000 -0.1009 0.02054 0.01588 -0.0874 0.8120 0.0256
-4.750 -0.0749 0.01747 0.01232 -0.0878 0.8010 0.0247
-4.500 -0.0474 0.01553 0.01001 -0.0878 0.7896 0.0245
-4.250 -0.0196 0.01425 0.00843 -0.0877 0.7784 0.0246
-4.000 0.0081 0.01332 0.00726 -0.0875 0.7672 0.0249
-3.750 0.0363 0.01272 0.00649 -0.0873 0.7553 0.0256
-3.500 0.0645 0.01224 0.00586 -0.0871 0.7435 0.0261
-3.250 0.0923 0.01128 0.00478 -0.0870 0.7319 0.0267
-3.000 0.1202 0.01075 0.00417 -0.0868 0.7202 0.0276
-2.750 0.1486 0.01039 0.00376 -0.0867 0.7080 0.0287
-2.500 0.1770 0.01009 0.00339 -0.0866 0.6958 0.0301
-2.250 0.2054 0.00986 0.00307 -0.0865 0.6838 0.0316
-2.000 0.2338 0.00956 0.00273 -0.0864 0.6721 0.0352
-1.750 0.2624 0.00934 0.00248 -0.0863 0.6598 0.0418
-1.500 0.2911 0.00908 0.00227 -0.0863 0.6478 0.0691
-1.250 0.3195 0.00897 0.00218 -0.0863 0.6362 0.0902
-1.000 0.3478 0.00891 0.00210 -0.0862 0.6247 0.1081
-0.750 0.3762 0.00880 0.00204 -0.0862 0.6129 0.1352
-0.500 0.4046 0.00864 0.00199 -0.0863 0.6016 0.1841
-0.250 0.4329 0.00838 0.00197 -0.0864 0.5907 0.2828
0.000 0.4609 0.00791 0.00202 -0.0867 0.5799 0.4755
0.250 0.4863 0.00725 0.00212 -0.0862 0.5694 0.7387
0.500 0.5081 0.00679 0.00209 -0.0841 0.5596 1.0000
0.750 0.5366 0.00691 0.00208 -0.0840 0.5493 1.0000
1.000 0.5651 0.00701 0.00209 -0.0840 0.5392 1.0000
1.250 0.5935 0.00714 0.00212 -0.0840 0.5297 1.0000
1.500 0.6219 0.00726 0.00215 -0.0839 0.5199 1.0000
1.750 0.6502 0.00738 0.00220 -0.0839 0.5106 1.0000
2.000 0.6783 0.00753 0.00225 -0.0838 0.5015 1.0000
2.250 0.7067 0.00764 0.00232 -0.0838 0.4921 1.0000
2.500 0.7347 0.00780 0.00239 -0.0837 0.4835 1.0000
2.750 0.7629 0.00792 0.00247 -0.0837 0.4740 1.0000
3.000 0.7909 0.00807 0.00257 -0.0836 0.4652 1.0000
3.250 0.8188 0.00823 0.00266 -0.0835 0.4560 1.0000
3.500 0.8468 0.00836 0.00277 -0.0835 0.4470 1.0000
3.750 0.8743 0.00855 0.00289 -0.0834 0.4383 1.0000
4.000 0.9024 0.00867 0.00301 -0.0833 0.4292 1.0000
4.250 0.9299 0.00885 0.00314 -0.0832 0.4206 1.0000
4.500 0.9575 0.00901 0.00328 -0.0831 0.4112 1.0000
4.750 0.9851 0.00917 0.00343 -0.0830 0.4021 1.0000
5.250 1.0397 0.00954 0.00374 -0.0828 0.3819 1.0000
5.500 1.0668 0.00973 0.00391 -0.0827 0.3714 1.0000
5.750 1.0936 0.00996 0.00410 -0.0825 0.3603 1.0000
6.000 1.1205 0.01016 0.00429 -0.0824 0.3490 1.0000
6.250 1.1473 0.01038 0.00450 -0.0822 0.3373 1.0000
6.500 1.1737 0.01062 0.00472 -0.0820 0.3244 1.0000
6.750 1.1998 0.01090 0.00496 -0.0818 0.3111 1.0000
7.000 1.2257 0.01119 0.00524 -0.0816 0.2967 1.0000
7.250 1.2512 0.01153 0.00552 -0.0813 0.2799 1.0000
7.500 1.2760 0.01193 0.00585 -0.0809 0.2610 1.0000
7.750 1.3001 0.01240 0.00623 -0.0805 0.2420 1.0000
8.000 1.3241 0.01287 0.00664 -0.0801 0.2220 1.0000
8.250 1.3470 0.01345 0.00712 -0.0796 0.2008 1.0000
8.500 1.3694 0.01404 0.00763 -0.0790 0.1811 1.0000
8.750 1.3915 0.01465 0.00817 -0.0783 0.1633 1.0000
9.000 1.4130 0.01530 0.00874 -0.0776 0.1473 1.0000
9.250 1.4339 0.01597 0.00935 -0.0769 0.1328 1.0000
9.500 1.4542 0.01665 0.00998 -0.0760 0.1201 1.0000
9.750 1.4741 0.01732 0.01064 -0.0751 0.1097 1.0000
10.000 1.4929 0.01806 0.01135 -0.0741 0.1007 1.0000
10.250 1.5110 0.01878 0.01206 -0.0730 0.0931 1.0000
10.500 1.5286 0.01950 0.01280 -0.0718 0.0874 1.0000
10.750 1.5448 0.02025 0.01356 -0.0704 0.0823 1.0000
11.000 1.5572 0.02117 0.01451 -0.0686 0.0776 1.0000
11.250 1.5709 0.02182 0.01523 -0.0668 0.0746 1.0000
11.500 1.5799 0.02269 0.01614 -0.0645 0.0715 1.0000
11.750 1.5838 0.02392 0.01739 -0.0619 0.0685 1.0000
12.000 1.5897 0.02513 0.01869 -0.0597 0.0664 1.0000
12.250 1.6000 0.02615 0.01980 -0.0583 0.0643 1.0000
12.500 1.6084 0.02737 0.02109 -0.0568 0.0619 1.0000
12.750 1.6126 0.02898 0.02274 -0.0554 0.0596 1.0000
13.000 1.6091 0.03138 0.02518 -0.0538 0.0570 1.0000
13.250 1.6189 0.03278 0.02669 -0.0530 0.0556 1.0000
13.500 1.6265 0.03443 0.02844 -0.0523 0.0539 1.0000
13.750 1.6319 0.03638 0.03048 -0.0518 0.0522 1.0000
14.000 1.6340 0.03873 0.03290 -0.0513 0.0507 1.0000
14.250 1.6320 0.04164 0.03587 -0.0510 0.0492 1.0000
14.500 1.6239 0.04536 0.03966 -0.0509 0.0476 1.0000
14.750 1.6279 0.04778 0.04221 -0.0509 0.0468 1.0000
15.000 1.6323 0.05026 0.04480 -0.0511 0.0455 1.0000
15.250 1.6342 0.05309 0.04773 -0.0515 0.0442 1.0000
15.500 1.6340 0.05624 0.05098 -0.0519 0.0430 1.0000
15.750 1.6316 0.05980 0.05461 -0.0527 0.0419 1.0000
16.000 1.6261 0.06387 0.05877 -0.0536 0.0409 1.0000
16.250 1.6164 0.06861 0.06358 -0.0549 0.0397 1.0000
16.500 1.6132 0.07256 0.06764 -0.0560 0.0389 1.0000
16.750 1.6138 0.07613 0.07135 -0.0571 0.0380 1.0000
17.000 1.6124 0.08000 0.07533 -0.0584 0.0370 1.0000
17.250 1.6100 0.08413 0.07956 -0.0599 0.0361 1.0000
17.500 1.6066 0.08846 0.08398 -0.0615 0.0351 1.0000
17.750 1.6010 0.09327 0.08888 -0.0635 0.0342 1.0000
18.000 1.5928 0.09849 0.09416 -0.0656 0.0333 1.0000
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Polar data table (+)
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