S4061-096-84 (s4061-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S4061-096-84 (s4061-il) Reynolds number: 100,000 Max Cl/Cd: 59.74 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4061-il-100000.txt Download as CSV file: xf-s4061-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3165 0.10104 0.09633 -0.0338 1.0000 0.0888
-8.500 -0.3306 0.09998 0.09541 -0.0384 1.0000 0.0912
-8.250 -0.3492 0.09906 0.09467 -0.0408 1.0000 0.0917
-8.000 -0.3111 0.09233 0.08784 -0.0361 1.0000 0.0964
-7.750 -0.3127 0.09031 0.08591 -0.0352 1.0000 0.1003
-7.500 -0.3285 0.08940 0.08513 -0.0328 1.0000 0.1020
-7.250 -0.3538 0.08938 0.08526 -0.0284 1.0000 0.1026
-7.000 -0.3791 0.08917 0.08516 -0.0244 1.0000 0.1030
-6.750 -0.3967 0.08806 0.08414 -0.0225 1.0000 0.1033
-6.500 -0.4240 0.08700 0.08317 -0.0277 1.0000 0.1054
-6.250 -0.4228 0.08268 0.07888 -0.0307 0.9982 0.1069
-6.000 -0.4009 0.07977 0.07598 -0.0259 0.9950 0.1111
-5.750 -0.3678 0.07274 0.06879 -0.0443 0.9853 0.1215
-5.500 -0.3468 0.06961 0.06570 -0.0427 0.9800 0.1249
-5.250 -0.3110 0.06361 0.05950 -0.0554 0.9725 0.1369
-5.000 -0.2893 0.06060 0.05650 -0.0558 0.9654 0.1411
-4.750 -0.2347 0.04306 0.03770 -0.0764 0.9594 0.0801
-4.500 -0.2020 0.03579 0.02952 -0.0797 0.9530 0.0629
-4.250 -0.1651 0.03164 0.02476 -0.0827 0.9476 0.0607
-4.000 -0.1246 0.02884 0.02119 -0.0854 0.9430 0.0635
-3.750 -0.0934 0.02667 0.01849 -0.0862 0.9357 0.0659
-3.500 -0.0522 0.02472 0.01638 -0.0887 0.9313 0.0716
-3.250 -0.0216 0.02351 0.01501 -0.0892 0.9241 0.0824
-3.000 0.0165 0.02230 0.01381 -0.0910 0.9183 0.1119
-2.750 0.0541 0.02162 0.01320 -0.0930 0.9127 0.1666
-2.500 0.0846 0.02104 0.01281 -0.0938 0.9049 0.2146
-2.250 0.1280 0.02032 0.01230 -0.0966 0.9008 0.2814
-2.000 0.1503 0.01998 0.01221 -0.0958 0.8914 0.3447
-1.750 0.1878 0.01920 0.01197 -0.0974 0.8866 0.4675
-1.500 0.2060 0.01863 0.01212 -0.0951 0.8775 0.6428
-1.250 0.2618 0.01774 0.01167 -0.0988 0.8738 1.0000
-1.000 0.2913 0.01797 0.01162 -0.0991 0.8657 1.0000
-0.750 0.3237 0.01809 0.01150 -0.0998 0.8583 1.0000
-0.500 0.3496 0.01837 0.01160 -0.0996 0.8495 1.0000
-0.250 0.3824 0.01845 0.01150 -0.1001 0.8427 1.0000
0.000 0.4062 0.01878 0.01169 -0.0995 0.8332 1.0000
0.250 0.4393 0.01879 0.01156 -0.0999 0.8270 1.0000
0.500 0.4618 0.01916 0.01183 -0.0991 0.8168 1.0000
0.750 0.4950 0.01910 0.01166 -0.0993 0.8112 1.0000
1.000 0.5168 0.01949 0.01199 -0.0984 0.8005 1.0000
1.250 0.5500 0.01936 0.01177 -0.0985 0.7953 1.0000
1.500 0.5717 0.01975 0.01213 -0.0975 0.7841 1.0000
1.750 0.5976 0.01994 0.01228 -0.0969 0.7753 1.0000
2.000 0.6268 0.01990 0.01219 -0.0965 0.7676 1.0000
2.250 0.6507 0.02017 0.01244 -0.0956 0.7571 1.0000
2.500 0.6823 0.01989 0.01213 -0.0952 0.7509 1.0000
2.750 0.7058 0.02012 0.01237 -0.0942 0.7393 1.0000
3.000 0.7316 0.02019 0.01244 -0.0934 0.7290 1.0000
3.250 0.7621 0.01986 0.01207 -0.0927 0.7214 1.0000
3.500 0.7864 0.02000 0.01227 -0.0917 0.7094 1.0000
3.750 0.8123 0.02002 0.01231 -0.0908 0.6983 1.0000
4.000 0.8421 0.01970 0.01197 -0.0900 0.6896 1.0000
4.250 0.8683 0.01964 0.01197 -0.0891 0.6777 1.0000
4.500 0.8938 0.01965 0.01202 -0.0882 0.6648 1.0000
4.750 0.9198 0.01959 0.01201 -0.0872 0.6519 1.0000
5.000 0.9463 0.01950 0.01195 -0.0863 0.6387 1.0000
5.250 0.9729 0.01939 0.01190 -0.0854 0.6248 1.0000
5.500 0.9992 0.01928 0.01183 -0.0844 0.6097 1.0000
5.750 1.0253 0.01918 0.01176 -0.0834 0.5933 1.0000
6.000 1.0514 0.01907 0.01170 -0.0823 0.5759 1.0000
6.250 1.0776 0.01897 0.01158 -0.0813 0.5574 1.0000
6.500 1.1003 0.01908 0.01178 -0.0800 0.5345 1.0000
6.750 1.1244 0.01912 0.01181 -0.0788 0.5111 1.0000
7.000 1.1470 0.01927 0.01196 -0.0774 0.4848 1.0000
7.250 1.1679 0.01955 0.01222 -0.0760 0.4553 1.0000
7.500 1.1872 0.01998 0.01261 -0.0744 0.4230 1.0000
7.750 1.2050 0.02055 0.01315 -0.0726 0.3887 1.0000
8.000 1.2215 0.02128 0.01375 -0.0708 0.3548 1.0000
8.250 1.2366 0.02218 0.01449 -0.0690 0.3222 1.0000
8.500 1.2504 0.02319 0.01541 -0.0671 0.2906 1.0000
8.750 1.2632 0.02434 0.01644 -0.0651 0.2614 1.0000
9.000 1.2746 0.02560 0.01758 -0.0630 0.2344 1.0000
9.250 1.2845 0.02693 0.01883 -0.0608 0.2088 1.0000
9.500 1.2915 0.02828 0.02015 -0.0584 0.1839 1.0000
9.750 1.2949 0.02968 0.02145 -0.0556 0.1621 1.0000
10.000 1.2956 0.03109 0.02285 -0.0526 0.1422 1.0000
10.250 1.2963 0.03281 0.02445 -0.0500 0.1251 1.0000
10.500 1.2976 0.03476 0.02639 -0.0476 0.1083 1.0000
10.750 1.2989 0.03692 0.02854 -0.0454 0.0931 1.0000
11.000 1.3011 0.03927 0.03089 -0.0434 0.0804 1.0000
11.250 1.3058 0.04168 0.03327 -0.0418 0.0705 1.0000
11.500 1.3191 0.04423 0.03565 -0.0405 0.0622 1.0000
11.750 1.3311 0.04665 0.03839 -0.0390 0.0576 1.0000
12.000 1.3438 0.04895 0.04074 -0.0379 0.0535 1.0000
12.250 1.3604 0.05210 0.04401 -0.0371 0.0500 1.0000
12.500 1.3641 0.05499 0.04724 -0.0357 0.0481 1.0000
12.750 1.3679 0.05829 0.05085 -0.0344 0.0467 1.0000
13.000 1.3681 0.06183 0.05470 -0.0333 0.0458 1.0000
13.250 1.3639 0.06563 0.05879 -0.0324 0.0452 1.0000
13.500 1.3553 0.06981 0.06327 -0.0317 0.0448 1.0000
13.750 1.3416 0.07446 0.06823 -0.0316 0.0447 1.0000
14.000 1.3229 0.07972 0.07379 -0.0321 0.0448 1.0000
14.250 1.2991 0.08579 0.08017 -0.0335 0.0451 1.0000
14.500 1.2716 0.09273 0.08742 -0.0361 0.0455 1.0000
14.750 1.2411 0.10076 0.09571 -0.0400 0.0461 1.0000
15.000 1.2088 0.11000 0.10519 -0.0454 0.0469 1.0000
15.250 1.1746 0.12085 0.11625 -0.0524 0.0479 1.0000
15.500 1.1398 0.13339 0.12892 -0.0609 0.0491 1.0000
15.750 1.1108 0.14620 0.14179 -0.0691 0.0503 1.0000
16.000 1.0943 0.15673 0.15232 -0.0751 0.0512 1.0000
16.250 1.0412 0.18703 0.18244 -0.0927 0.0632 1.0000
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Polar data table (+)
Polar graphs
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