S4061-096-84 (s4061-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4061-096-84 (s4061-il) Reynolds number: 500,000 Max Cl/Cd: 116.6 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4061-il-500000.txt Download as CSV file: xf-s4061-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S4061-096-84
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3379 0.09472 0.09254 -0.0357 1.0000 0.0203
-9.000 -0.3346 0.09096 0.08882 -0.0381 1.0000 0.0204
-8.750 -0.3385 0.08583 0.08375 -0.0405 1.0000 0.0207
-8.500 -0.3323 0.08373 0.08167 -0.0402 1.0000 0.0212
-8.250 -0.3172 0.08144 0.07940 -0.0421 0.9872 0.0218
-8.000 -0.2955 0.07712 0.07507 -0.0485 0.9723 0.0226
-7.750 -0.2771 0.07228 0.07020 -0.0555 0.9545 0.0236
-7.500 -0.2742 0.06838 0.06625 -0.0589 0.9314 0.0242
-7.000 -0.2704 0.05376 0.05141 -0.0758 0.8953 0.0261
-6.750 -0.2779 0.04280 0.04005 -0.0833 0.8830 0.0267
-6.500 -0.2629 0.04046 0.03769 -0.0838 0.8747 0.0273
-6.250 -0.2458 0.03811 0.03523 -0.0847 0.8673 0.0279
-6.000 -0.2402 0.02217 0.01747 -0.0876 0.8586 0.0160
-5.750 -0.2187 0.01849 0.01340 -0.0875 0.8524 0.0153
-5.500 -0.1934 0.01656 0.01110 -0.0873 0.8457 0.0153
-5.250 -0.1675 0.01527 0.00951 -0.0868 0.8401 0.0155
-5.000 -0.1404 0.01432 0.00838 -0.0867 0.8333 0.0158
-4.750 -0.1141 0.01321 0.00708 -0.0863 0.8274 0.0162
-4.500 -0.0877 0.01220 0.00599 -0.0861 0.8212 0.0169
-4.250 -0.0604 0.01175 0.00550 -0.0860 0.8147 0.0183
-4.000 -0.0331 0.01126 0.00491 -0.0858 0.8091 0.0194
-3.750 -0.0052 0.01078 0.00435 -0.0857 0.8022 0.0203
-3.500 0.0222 0.01019 0.00368 -0.0855 0.7964 0.0227
-3.250 0.0504 0.00983 0.00326 -0.0854 0.7898 0.0269
-3.000 0.0780 0.00924 0.00281 -0.0853 0.7835 0.0618
-2.750 0.1058 0.00900 0.00264 -0.0853 0.7773 0.0929
-2.500 0.1339 0.00879 0.00248 -0.0853 0.7706 0.1196
-2.250 0.1616 0.00860 0.00235 -0.0853 0.7647 0.1529
-2.000 0.1897 0.00838 0.00226 -0.0854 0.7576 0.1953
-1.750 0.2175 0.00819 0.00215 -0.0853 0.7514 0.2399
-1.500 0.2456 0.00800 0.00208 -0.0854 0.7445 0.2862
-1.250 0.2733 0.00779 0.00201 -0.0854 0.7379 0.3447
-1.000 0.3010 0.00756 0.00197 -0.0854 0.7312 0.4175
-0.750 0.3283 0.00728 0.00195 -0.0853 0.7242 0.5126
-0.500 0.3548 0.00698 0.00195 -0.0851 0.7176 0.6250
-0.250 0.3788 0.00655 0.00198 -0.0840 0.7103 0.7714
0.000 0.4115 0.00614 0.00191 -0.0843 0.7038 0.9863
0.250 0.4413 0.00617 0.00187 -0.0847 0.6959 1.0000
0.500 0.4692 0.00624 0.00185 -0.0846 0.6887 1.0000
0.750 0.4972 0.00629 0.00184 -0.0846 0.6804 1.0000
1.000 0.5252 0.00636 0.00184 -0.0845 0.6722 1.0000
1.250 0.5530 0.00643 0.00183 -0.0844 0.6630 1.0000
1.500 0.5810 0.00649 0.00185 -0.0843 0.6534 1.0000
1.750 0.6087 0.00658 0.00187 -0.0843 0.6447 1.0000
2.000 0.6366 0.00666 0.00190 -0.0842 0.6349 1.0000
2.250 0.6644 0.00674 0.00196 -0.0841 0.6252 1.0000
2.500 0.6920 0.00685 0.00200 -0.0840 0.6156 1.0000
2.750 0.7197 0.00694 0.00206 -0.0840 0.6048 1.0000
3.000 0.7474 0.00704 0.00214 -0.0839 0.5942 1.0000
3.250 0.7749 0.00716 0.00223 -0.0838 0.5834 1.0000
3.500 0.8022 0.00729 0.00231 -0.0837 0.5720 1.0000
3.750 0.8296 0.00741 0.00241 -0.0836 0.5595 1.0000
4.000 0.8568 0.00755 0.00252 -0.0835 0.5463 1.0000
4.250 0.8839 0.00770 0.00266 -0.0833 0.5325 1.0000
4.500 0.9107 0.00787 0.00279 -0.0832 0.5176 1.0000
4.750 0.9373 0.00805 0.00294 -0.0830 0.5015 1.0000
5.250 0.9899 0.00849 0.00331 -0.0825 0.4653 1.0000
5.500 1.0157 0.00875 0.00351 -0.0822 0.4438 1.0000
5.750 1.0410 0.00905 0.00375 -0.0819 0.4202 1.0000
6.000 1.0655 0.00943 0.00402 -0.0814 0.3909 1.0000
6.250 1.0893 0.00986 0.00434 -0.0809 0.3582 1.0000
6.500 1.1127 0.01034 0.00468 -0.0804 0.3263 1.0000
6.750 1.1353 0.01089 0.00509 -0.0797 0.2933 1.0000
7.000 1.1577 0.01145 0.00552 -0.0791 0.2616 1.0000
7.250 1.1794 0.01206 0.00598 -0.0784 0.2303 1.0000
7.500 1.2007 0.01269 0.00646 -0.0776 0.2010 1.0000
7.750 1.2220 0.01328 0.00696 -0.0768 0.1778 1.0000
8.000 1.2430 0.01388 0.00747 -0.0760 0.1547 1.0000
8.250 1.2634 0.01451 0.00800 -0.0751 0.1332 1.0000
8.500 1.2829 0.01519 0.00858 -0.0741 0.1129 1.0000
8.750 1.3020 0.01587 0.00919 -0.0730 0.0947 1.0000
9.000 1.3198 0.01660 0.00984 -0.0718 0.0775 1.0000
9.250 1.3361 0.01741 0.01057 -0.0704 0.0619 1.0000
9.500 1.3513 0.01825 0.01134 -0.0688 0.0470 1.0000
9.750 1.3612 0.01937 0.01236 -0.0664 0.0313 1.0000
10.000 1.3682 0.02045 0.01343 -0.0635 0.0233 1.0000
10.500 1.3843 0.02255 0.01563 -0.0586 0.0183 1.0000
10.750 1.3935 0.02361 0.01675 -0.0566 0.0169 1.0000
11.000 1.3992 0.02497 0.01816 -0.0544 0.0158 1.0000
11.250 1.4008 0.02672 0.02001 -0.0521 0.0151 1.0000
11.500 1.4081 0.02811 0.02151 -0.0504 0.0146 1.0000
11.750 1.4139 0.02969 0.02319 -0.0488 0.0142 1.0000
12.000 1.4189 0.03140 0.02502 -0.0473 0.0137 1.0000
12.250 1.4229 0.03327 0.02699 -0.0459 0.0134 1.0000
12.500 1.4264 0.03527 0.02909 -0.0448 0.0130 1.0000
12.750 1.4285 0.03747 0.03138 -0.0437 0.0127 1.0000
13.000 1.4294 0.03988 0.03389 -0.0428 0.0124 1.0000
13.250 1.4289 0.04255 0.03665 -0.0420 0.0122 1.0000
13.500 1.4259 0.04556 0.03975 -0.0413 0.0119 1.0000
13.750 1.4208 0.04894 0.04325 -0.0408 0.0116 1.0000
14.000 1.4137 0.05268 0.04711 -0.0402 0.0114 1.0000
14.250 1.4169 0.05533 0.04990 -0.0403 0.0112 1.0000
14.500 1.4172 0.05841 0.05311 -0.0404 0.0111 1.0000
14.750 1.4172 0.06166 0.05649 -0.0407 0.0109 1.0000
15.000 1.4161 0.06515 0.06012 -0.0411 0.0107 1.0000
15.250 1.4143 0.06883 0.06394 -0.0418 0.0106 1.0000
15.500 1.4114 0.07277 0.06802 -0.0425 0.0105 1.0000
15.750 1.4080 0.07691 0.07230 -0.0436 0.0103 1.0000
16.000 1.4039 0.08131 0.07684 -0.0448 0.0102 1.0000
16.250 1.3984 0.08601 0.08169 -0.0463 0.0101 1.0000
16.500 1.3928 0.09091 0.08673 -0.0481 0.0100 1.0000
16.750 1.3858 0.09614 0.09212 -0.0502 0.0099 1.0000
17.000 1.3781 0.10167 0.09779 -0.0526 0.0098 1.0000
17.250 1.3697 0.10746 0.10374 -0.0553 0.0097 1.0000
17.500 1.3597 0.11375 0.11019 -0.0584 0.0097 1.0000
17.750 1.3495 0.12022 0.11682 -0.0618 0.0096 1.0000
18.000 1.3380 0.12716 0.12391 -0.0657 0.0096 1.0000
18.250 1.3258 0.13446 0.13138 -0.0699 0.0096 1.0000
18.500 1.3125 0.14223 0.13931 -0.0747 0.0096 1.0000
18.750 1.2976 0.15070 0.14796 -0.0800 0.0096 1.0000
19.000 1.2799 0.16024 0.15768 -0.0863 0.0097 1.0000
19.250 1.2569 0.17173 0.16937 -0.0940 0.0098 1.0000
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Polar data table (+)
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