S4180-098-84 (s4180-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4180-098-84 (s4180-il) Reynolds number: 500,000 Max Cl/Cd: 104.39 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4180-il-500000-n5.txt Download as CSV file: xf-s4180-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3305 0.10360 0.10127 -0.0214 1.0000 0.0142
-9.500 -0.3277 0.09954 0.09723 -0.0233 1.0000 0.0135
-9.250 -0.3220 0.09641 0.09411 -0.0245 1.0000 0.0134
-9.000 -0.3163 0.09342 0.09114 -0.0256 1.0000 0.0132
-8.750 -0.3118 0.09030 0.08805 -0.0269 1.0000 0.0130
-8.500 -0.3015 0.08592 0.08368 -0.0309 0.9690 0.0129
-8.250 -0.2808 0.07969 0.07739 -0.0395 0.9356 0.0131
-8.000 -0.2709 0.07577 0.07337 -0.0432 0.9012 0.0129
-7.750 -0.2722 0.07221 0.06973 -0.0446 0.8726 0.0129
-6.750 -0.2955 0.02047 0.01574 -0.0857 0.8043 0.0134
-6.500 -0.2701 0.01875 0.01363 -0.0860 0.7930 0.0136
-6.250 -0.2438 0.01757 0.01213 -0.0861 0.7818 0.0137
-6.000 -0.2176 0.01612 0.01040 -0.0863 0.7703 0.0140
-5.750 -0.1907 0.01521 0.00931 -0.0863 0.7587 0.0143
-5.500 -0.1634 0.01451 0.00847 -0.0863 0.7476 0.0145
-5.250 -0.1360 0.01391 0.00771 -0.0862 0.7359 0.0148
-5.000 -0.1083 0.01335 0.00702 -0.0862 0.7241 0.0151
-4.750 -0.0804 0.01286 0.00640 -0.0861 0.7124 0.0155
-4.500 -0.0525 0.01244 0.00586 -0.0860 0.7010 0.0161
-4.000 0.0037 0.01168 0.00485 -0.0858 0.6772 0.0170
-3.750 0.0319 0.01134 0.00441 -0.0858 0.6659 0.0173
-3.500 0.0601 0.01090 0.00388 -0.0857 0.6548 0.0178
-3.250 0.0883 0.01061 0.00352 -0.0857 0.6430 0.0185
-3.000 0.1168 0.01038 0.00323 -0.0857 0.6317 0.0192
-2.750 0.1452 0.01019 0.00295 -0.0856 0.6211 0.0200
-2.500 0.1736 0.01003 0.00271 -0.0855 0.6099 0.0209
-2.250 0.2022 0.00986 0.00248 -0.0855 0.5987 0.0224
-2.000 0.2307 0.00971 0.00230 -0.0855 0.5884 0.0249
-1.750 0.2591 0.00959 0.00213 -0.0854 0.5779 0.0293
-1.500 0.2876 0.00944 0.00201 -0.0854 0.5671 0.0423
-1.250 0.3161 0.00936 0.00192 -0.0854 0.5572 0.0568
-1.000 0.3445 0.00931 0.00186 -0.0854 0.5472 0.0695
-0.750 0.3730 0.00923 0.00181 -0.0854 0.5371 0.0865
-0.500 0.4014 0.00918 0.00178 -0.0854 0.5278 0.1080
-0.250 0.4298 0.00912 0.00175 -0.0854 0.5181 0.1330
0.000 0.4583 0.00902 0.00174 -0.0855 0.5090 0.1740
0.250 0.4866 0.00890 0.00175 -0.0856 0.5003 0.2366
0.500 0.5151 0.00876 0.00177 -0.0857 0.4913 0.3081
0.750 0.5433 0.00859 0.00182 -0.0858 0.4830 0.4054
1.000 0.5714 0.00832 0.00189 -0.0859 0.4745 0.5444
1.250 0.5979 0.00795 0.00200 -0.0856 0.4666 0.7234
1.500 0.6155 0.00752 0.00205 -0.0828 0.4590 0.9265
1.750 0.6473 0.00758 0.00206 -0.0835 0.4509 1.0000
2.000 0.6756 0.00771 0.00211 -0.0834 0.4425 1.0000
2.250 0.7039 0.00784 0.00218 -0.0834 0.4346 1.0000
2.500 0.7320 0.00797 0.00225 -0.0834 0.4261 1.0000
2.750 0.7601 0.00811 0.00233 -0.0833 0.4177 1.0000
3.000 0.7880 0.00827 0.00243 -0.0833 0.4087 1.0000
3.250 0.8161 0.00840 0.00252 -0.0832 0.3998 1.0000
3.500 0.8438 0.00858 0.00263 -0.0831 0.3908 1.0000
3.750 0.8716 0.00873 0.00275 -0.0831 0.3814 1.0000
4.000 0.8993 0.00890 0.00288 -0.0830 0.3724 1.0000
4.250 0.9268 0.00909 0.00302 -0.0829 0.3627 1.0000
4.500 0.9543 0.00926 0.00316 -0.0828 0.3528 1.0000
4.750 0.9816 0.00946 0.00332 -0.0827 0.3423 1.0000
5.000 1.0086 0.00969 0.00350 -0.0826 0.3303 1.0000
5.250 1.0355 0.00992 0.00368 -0.0824 0.3172 1.0000
5.500 1.0622 0.01018 0.00389 -0.0823 0.3028 1.0000
5.750 1.0885 0.01047 0.00411 -0.0821 0.2870 1.0000
6.250 1.1407 0.01110 0.00462 -0.0817 0.2560 1.0000
6.500 1.1662 0.01147 0.00492 -0.0814 0.2382 1.0000
6.750 1.1914 0.01187 0.00524 -0.0811 0.2207 1.0000
7.000 1.2163 0.01228 0.00559 -0.0808 0.2043 1.0000
7.250 1.2406 0.01275 0.00598 -0.0804 0.1870 1.0000
7.500 1.2645 0.01326 0.00640 -0.0800 0.1700 1.0000
7.750 1.2883 0.01374 0.00683 -0.0795 0.1555 1.0000
8.250 1.3353 0.01474 0.00773 -0.0786 0.1305 1.0000
8.500 1.3582 0.01525 0.00821 -0.0780 0.1191 1.0000
8.750 1.3810 0.01576 0.00870 -0.0775 0.1099 1.0000
9.000 1.4030 0.01631 0.00922 -0.0768 0.1015 1.0000
9.250 1.4249 0.01684 0.00975 -0.0761 0.0937 1.0000
9.500 1.4462 0.01739 0.01030 -0.0754 0.0869 1.0000
9.750 1.4666 0.01799 0.01089 -0.0746 0.0807 1.0000
10.000 1.4869 0.01856 0.01148 -0.0737 0.0759 1.0000
10.250 1.5062 0.01916 0.01211 -0.0727 0.0711 1.0000
10.500 1.5240 0.01985 0.01280 -0.0716 0.0670 1.0000
10.750 1.5424 0.02042 0.01344 -0.0705 0.0642 1.0000
11.000 1.5584 0.02111 0.01416 -0.0691 0.0609 1.0000
11.250 1.5701 0.02188 0.01496 -0.0671 0.0580 1.0000
11.500 1.5811 0.02264 0.01577 -0.0650 0.0560 1.0000
11.750 1.5922 0.02342 0.01663 -0.0631 0.0543 1.0000
12.000 1.6017 0.02436 0.01764 -0.0613 0.0525 1.0000
12.250 1.6097 0.02547 0.01880 -0.0595 0.0505 1.0000
12.500 1.6157 0.02682 0.02019 -0.0578 0.0482 1.0000
12.750 1.6237 0.02810 0.02154 -0.0565 0.0465 1.0000
13.000 1.6319 0.02944 0.02297 -0.0553 0.0447 1.0000
13.250 1.6383 0.03103 0.02463 -0.0543 0.0428 1.0000
13.500 1.6426 0.03289 0.02655 -0.0533 0.0412 1.0000
13.750 1.6455 0.03500 0.02873 -0.0525 0.0397 1.0000
14.000 1.6498 0.03706 0.03088 -0.0520 0.0387 1.0000
14.250 1.6543 0.03919 0.03312 -0.0516 0.0377 1.0000
14.500 1.6574 0.04155 0.03557 -0.0513 0.0365 1.0000
14.750 1.6588 0.04419 0.03829 -0.0512 0.0353 1.0000
15.000 1.6582 0.04713 0.04131 -0.0513 0.0339 1.0000
15.250 1.6558 0.05041 0.04467 -0.0517 0.0328 1.0000
15.500 1.6538 0.05375 0.04811 -0.0521 0.0319 1.0000
15.750 1.6531 0.05697 0.05145 -0.0526 0.0311 1.0000
16.000 1.6510 0.06049 0.05509 -0.0533 0.0301 1.0000
16.250 1.6478 0.06429 0.05897 -0.0543 0.0290 1.0000
16.500 1.6432 0.06836 0.06314 -0.0554 0.0281 1.0000
16.750 1.6372 0.07278 0.06765 -0.0567 0.0272 1.0000
17.000 1.6293 0.07759 0.07256 -0.0583 0.0263 1.0000
17.250 1.6249 0.08197 0.07705 -0.0598 0.0257 1.0000
17.500 1.6196 0.08656 0.08176 -0.0615 0.0249 1.0000
17.750 1.6134 0.09141 0.08672 -0.0634 0.0241 1.0000
18.000 1.6062 0.09647 0.09189 -0.0654 0.0233 1.0000
18.250 1.5979 0.10184 0.09735 -0.0677 0.0225 1.0000
18.500 1.5887 0.10744 0.10305 -0.0702 0.0218 1.0000
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Polar data table (+)
Polar graphs
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