S4158 (s4158-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4158 (s4158-il) Reynolds number: 200,000 Max Cl/Cd: 80.83 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4158-il-200000-n5.txt Download as CSV file: xf-s4158-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4158
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3201 0.11582 0.11197 -0.0467 0.8856 0.0283
-10.750 -0.3158 0.11222 0.10838 -0.0491 0.8835 0.0285
-10.500 -0.3131 0.10857 0.10474 -0.0518 0.8812 0.0286
-10.250 -0.3088 0.10493 0.10110 -0.0538 0.8790 0.0287
-10.000 -0.3050 0.10113 0.09729 -0.0557 0.8769 0.0287
-9.750 -0.3013 0.09737 0.09352 -0.0574 0.8748 0.0288
-9.500 -0.2395 0.08303 0.07940 -0.0540 0.8623 0.0223
-9.250 -0.2908 0.08826 0.08441 -0.0586 0.8710 0.0210
-9.000 -0.2855 0.08518 0.08134 -0.0598 0.8688 0.0202
-8.750 -0.2839 0.08150 0.07767 -0.0616 0.8662 0.0193
-8.250 -0.3084 0.06769 0.06391 -0.0706 0.8595 0.0161
-8.000 -0.3149 0.06271 0.05896 -0.0752 0.8555 0.0160
-7.750 -0.3157 0.05756 0.05374 -0.0792 0.8522 0.0158
-7.500 -0.3160 0.05207 0.04808 -0.0822 0.8493 0.0155
-7.250 -0.3152 0.04650 0.04227 -0.0839 0.8469 0.0153
-7.000 -0.3103 0.04086 0.03628 -0.0853 0.8437 0.0151
-6.750 -0.3018 0.03589 0.03086 -0.0856 0.8406 0.0149
-6.500 -0.2900 0.03161 0.02604 -0.0851 0.8379 0.0149
-6.250 -0.2740 0.02829 0.02217 -0.0843 0.8357 0.0151
-6.000 -0.2548 0.02572 0.01909 -0.0834 0.8338 0.0154
-5.750 -0.2330 0.02386 0.01680 -0.0826 0.8320 0.0158
-5.500 -0.2089 0.02244 0.01510 -0.0824 0.8292 0.0168
-5.250 -0.1843 0.02147 0.01401 -0.0823 0.8266 0.0176
-5.000 -0.1594 0.02047 0.01282 -0.0819 0.8242 0.0183
-4.750 -0.1344 0.01946 0.01165 -0.0814 0.8221 0.0187
-4.500 -0.1095 0.01858 0.01062 -0.0808 0.8202 0.0193
-4.250 -0.0845 0.01780 0.00972 -0.0802 0.8185 0.0201
-4.000 -0.0589 0.01718 0.00901 -0.0799 0.8158 0.0211
-3.750 -0.0336 0.01660 0.00836 -0.0797 0.8127 0.0223
-3.500 -0.0081 0.01613 0.00785 -0.0794 0.8099 0.0244
-3.250 0.0180 0.01580 0.00745 -0.0790 0.8076 0.0285
-3.000 0.0436 0.01533 0.00697 -0.0785 0.8055 0.0355
-2.750 0.0694 0.01489 0.00653 -0.0781 0.8037 0.0510
-2.500 0.0953 0.01463 0.00637 -0.0780 0.7999 0.0774
-2.250 0.1204 0.01424 0.00623 -0.0778 0.7964 0.1329
-2.000 0.1447 0.01370 0.00605 -0.0774 0.7935 0.2263
-1.750 0.1692 0.01320 0.00588 -0.0769 0.7911 0.3306
-1.500 0.1931 0.01272 0.00573 -0.0762 0.7891 0.4419
-1.250 0.2149 0.01238 0.00583 -0.0752 0.7841 0.5615
-1.000 0.2363 0.01196 0.00582 -0.0737 0.7804 0.6867
-0.750 0.2631 0.01154 0.00577 -0.0727 0.7777 0.8230
-0.500 0.3263 0.01130 0.00561 -0.0794 0.7763 0.9415
-0.250 0.3791 0.01118 0.00537 -0.0843 0.7746 0.9856
0.000 0.4196 0.01124 0.00538 -0.0873 0.7691 1.0000
0.250 0.4437 0.01122 0.00528 -0.0866 0.7645 1.0000
0.500 0.4684 0.01114 0.00511 -0.0858 0.7612 1.0000
0.750 0.4926 0.01121 0.00515 -0.0853 0.7555 1.0000
1.000 0.5173 0.01122 0.00511 -0.0847 0.7505 1.0000
1.250 0.5427 0.01114 0.00498 -0.0840 0.7469 1.0000
1.500 0.5670 0.01123 0.00507 -0.0835 0.7407 1.0000
1.750 0.5921 0.01122 0.00503 -0.0829 0.7354 1.0000
2.000 0.6178 0.01115 0.00493 -0.0823 0.7313 1.0000
2.250 0.6420 0.01125 0.00506 -0.0818 0.7234 1.0000
2.500 0.6679 0.01117 0.00494 -0.0812 0.7185 1.0000
2.750 0.6922 0.01125 0.00507 -0.0806 0.7097 1.0000
3.000 0.7180 0.01117 0.00497 -0.0800 0.7031 1.0000
3.250 0.7429 0.01117 0.00498 -0.0794 0.6925 1.0000
3.500 0.7679 0.01112 0.00493 -0.0787 0.6800 1.0000
3.750 0.7931 0.01105 0.00486 -0.0780 0.6663 1.0000
4.000 0.8184 0.01102 0.00479 -0.0773 0.6517 1.0000
4.250 0.8436 0.01102 0.00475 -0.0767 0.6362 1.0000
4.500 0.8685 0.01108 0.00476 -0.0759 0.6195 1.0000
4.750 0.8926 0.01122 0.00487 -0.0752 0.6003 1.0000
5.000 0.9163 0.01139 0.00499 -0.0744 0.5798 1.0000
5.250 0.9393 0.01162 0.00516 -0.0735 0.5577 1.0000
5.500 0.9613 0.01192 0.00536 -0.0724 0.5334 1.0000
5.750 0.9818 0.01228 0.00565 -0.0712 0.5050 1.0000
6.000 0.9999 0.01276 0.00598 -0.0696 0.4694 1.0000
6.250 1.0158 0.01334 0.00637 -0.0677 0.4322 1.0000
6.500 1.0309 0.01395 0.00682 -0.0657 0.3961 1.0000
6.750 1.0447 0.01460 0.00732 -0.0636 0.3619 1.0000
7.000 1.0570 0.01529 0.00789 -0.0613 0.3265 1.0000
7.250 1.0678 0.01604 0.00848 -0.0589 0.2913 1.0000
7.500 1.0758 0.01682 0.00910 -0.0560 0.2594 1.0000
7.750 1.0835 0.01763 0.00979 -0.0532 0.2314 1.0000
8.000 1.0924 0.01849 0.01053 -0.0507 0.2046 1.0000
8.250 1.1025 0.01937 0.01131 -0.0485 0.1802 1.0000
8.500 1.1131 0.02027 0.01215 -0.0465 0.1584 1.0000
8.750 1.1237 0.02122 0.01301 -0.0446 0.1358 1.0000
9.000 1.1344 0.02220 0.01392 -0.0428 0.1153 1.0000
9.250 1.1447 0.02325 0.01488 -0.0409 0.0964 1.0000
9.500 1.1548 0.02434 0.01591 -0.0392 0.0818 1.0000
9.750 1.1652 0.02542 0.01697 -0.0375 0.0706 1.0000
10.000 1.1762 0.02650 0.01809 -0.0359 0.0623 1.0000
10.250 1.1857 0.02770 0.01930 -0.0343 0.0562 1.0000
10.500 1.1967 0.02881 0.02048 -0.0328 0.0508 1.0000
10.750 1.2041 0.03021 0.02187 -0.0312 0.0461 1.0000
11.000 1.2153 0.03134 0.02313 -0.0298 0.0426 1.0000
11.250 1.2241 0.03268 0.02454 -0.0284 0.0391 1.0000
11.500 1.2292 0.03435 0.02622 -0.0268 0.0361 1.0000
11.750 1.2394 0.03564 0.02768 -0.0256 0.0335 1.0000
12.000 1.2474 0.03713 0.02927 -0.0244 0.0312 1.0000
12.250 1.2533 0.03884 0.03103 -0.0232 0.0290 1.0000
12.500 1.2556 0.04092 0.03317 -0.0218 0.0273 1.0000
12.750 1.2640 0.04248 0.03489 -0.0209 0.0255 1.0000
13.000 1.2691 0.04439 0.03693 -0.0198 0.0241 1.0000
13.250 1.2735 0.04643 0.03907 -0.0189 0.0228 1.0000
13.500 1.2758 0.04875 0.04146 -0.0182 0.0215 1.0000
13.750 1.2750 0.05148 0.04426 -0.0174 0.0206 1.0000
14.000 1.2791 0.05380 0.04676 -0.0168 0.0197 1.0000
14.250 1.2825 0.05624 0.04938 -0.0164 0.0186 1.0000
14.500 1.2848 0.05888 0.05216 -0.0162 0.0177 1.0000
14.750 1.2861 0.06170 0.05510 -0.0162 0.0168 1.0000
15.000 1.2858 0.06483 0.05835 -0.0163 0.0163 1.0000
15.250 1.2837 0.06826 0.06189 -0.0166 0.0158 1.0000
15.500 1.2787 0.07217 0.06589 -0.0171 0.0152 1.0000
15.750 1.2768 0.07582 0.06971 -0.0176 0.0149 1.0000
16.000 1.2741 0.07971 0.07379 -0.0183 0.0145 1.0000
16.250 1.2703 0.08386 0.07814 -0.0193 0.0141 1.0000
16.500 1.2649 0.08837 0.08284 -0.0206 0.0138 1.0000
16.750 1.2591 0.09312 0.08777 -0.0223 0.0133 1.0000
17.000 1.2527 0.09806 0.09288 -0.0243 0.0130 1.0000
17.250 1.2446 0.10344 0.09844 -0.0265 0.0128 1.0000
17.500 1.2365 0.10898 0.10412 -0.0292 0.0125 1.0000
17.750 1.2274 0.11488 0.11019 -0.0321 0.0122 1.0000
18.000 1.2173 0.12113 0.11659 -0.0354 0.0121 1.0000
18.250 1.2079 0.12740 0.12299 -0.0389 0.0118 1.0000
18.500 1.1966 0.13423 0.12998 -0.0428 0.0117 1.0000
18.750 1.1842 0.14157 0.13747 -0.0471 0.0117 1.0000
19.000 1.1715 0.14923 0.14528 -0.0517 0.0116 1.0000
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Polar data table (+)
Polar graphs
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