S4083 (8%) (s4083-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S4083 (8%) (s4083-il) Reynolds number: 100,000 Max Cl/Cd: 51.8 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4083-il-100000.txt Download as CSV file: xf-s4083-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S4083 (8%)
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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3693 0.09162 0.08695 -0.0183 1.0000 0.0755
-7.000 -0.3745 0.08944 0.08487 -0.0191 1.0000 0.0780
-6.750 -0.3771 0.08722 0.08275 -0.0278 1.0000 0.0801
-6.500 -0.3726 0.08284 0.07842 -0.0323 1.0000 0.0811
-6.250 -0.3651 0.07946 0.07511 -0.0241 1.0000 0.0838
-6.000 -0.3576 0.07664 0.07233 -0.0238 1.0000 0.0879
-5.750 -0.3416 0.07275 0.06828 -0.0396 1.0000 0.0943
-5.500 -0.3400 0.06900 0.06474 -0.0321 1.0000 0.0970
-5.250 -0.3307 0.06646 0.06223 -0.0307 1.0000 0.1033
-5.000 -0.3145 0.06189 0.05758 -0.0374 1.0000 0.1106
-4.750 -0.3049 0.05941 0.05517 -0.0350 1.0000 0.1165
-4.500 -0.2866 0.05533 0.05099 -0.0394 1.0000 0.1257
-4.250 -0.2665 0.05186 0.04738 -0.0428 1.0000 0.1385
-4.000 -0.2551 0.04945 0.04504 -0.0405 1.0000 0.1450
-3.750 -0.2370 0.04644 0.04198 -0.0417 1.0000 0.1578
-3.500 -0.2186 0.04374 0.03921 -0.0425 1.0000 0.1732
-3.250 -0.1982 0.04114 0.03649 -0.0440 1.0000 0.1966
-3.000 -0.1275 0.03007 0.02361 -0.0531 1.0000 0.0786
-2.750 -0.0976 0.02645 0.01934 -0.0532 1.0000 0.0647
-2.500 -0.0722 0.02407 0.01660 -0.0529 1.0000 0.0612
-2.250 -0.0474 0.02246 0.01461 -0.0524 1.0000 0.0611
-2.000 -0.0252 0.02147 0.01332 -0.0515 1.0000 0.0644
-1.750 0.0259 0.01994 0.01137 -0.0555 0.9905 0.0669
-1.500 0.0776 0.01809 0.00955 -0.0598 0.9785 0.0795
-1.250 0.1280 0.01625 0.00813 -0.0640 0.9648 0.1462
-1.000 0.1771 0.01288 0.00742 -0.0671 0.9544 1.0000
-0.750 0.2341 0.01267 0.00676 -0.0724 0.9359 1.0000
-0.500 0.2869 0.01236 0.00613 -0.0768 0.9137 1.0000
-0.250 0.3418 0.01205 0.00554 -0.0814 0.8898 1.0000
0.000 0.3926 0.01183 0.00506 -0.0852 0.8583 1.0000
0.250 0.4392 0.01176 0.00468 -0.0882 0.8230 1.0000
0.500 0.4760 0.01191 0.00454 -0.0894 0.7860 1.0000
0.750 0.5078 0.01217 0.00451 -0.0896 0.7534 1.0000
1.000 0.5363 0.01249 0.00457 -0.0893 0.7250 1.0000
1.250 0.5632 0.01285 0.00470 -0.0888 0.6997 1.0000
1.500 0.5902 0.01322 0.00485 -0.0882 0.6783 1.0000
1.750 0.6157 0.01359 0.00507 -0.0876 0.6575 1.0000
2.000 0.6416 0.01397 0.00532 -0.0870 0.6393 1.0000
2.250 0.6676 0.01436 0.00556 -0.0864 0.6229 1.0000
2.500 0.6935 0.01477 0.00584 -0.0858 0.6075 1.0000
2.750 0.7192 0.01517 0.00615 -0.0852 0.5927 1.0000
3.000 0.7447 0.01558 0.00651 -0.0846 0.5785 1.0000
3.250 0.7700 0.01598 0.00687 -0.0840 0.5646 1.0000
3.500 0.7951 0.01639 0.00725 -0.0834 0.5511 1.0000
3.750 0.8201 0.01681 0.00766 -0.0827 0.5379 1.0000
4.000 0.8451 0.01724 0.00810 -0.0821 0.5251 1.0000
4.250 0.8700 0.01768 0.00860 -0.0814 0.5127 1.0000
4.500 0.8950 0.01813 0.00907 -0.0808 0.5006 1.0000
4.750 0.9200 0.01859 0.00954 -0.0801 0.4888 1.0000
5.000 0.9453 0.01904 0.00998 -0.0795 0.4771 1.0000
5.250 0.9699 0.01947 0.01049 -0.0787 0.4647 1.0000
5.500 0.9938 0.01991 0.01102 -0.0779 0.4518 1.0000
5.750 1.0177 0.02036 0.01156 -0.0770 0.4388 1.0000
6.000 1.0414 0.02080 0.01209 -0.0762 0.4256 1.0000
6.250 1.0650 0.02124 0.01266 -0.0752 0.4122 1.0000
6.500 1.0884 0.02165 0.01316 -0.0743 0.3983 1.0000
6.750 1.1115 0.02202 0.01362 -0.0732 0.3836 1.0000
7.000 1.1343 0.02237 0.01405 -0.0721 0.3684 1.0000
7.250 1.1569 0.02271 0.01450 -0.0710 0.3527 1.0000
7.500 1.1795 0.02303 0.01485 -0.0698 0.3364 1.0000
7.750 1.1989 0.02339 0.01543 -0.0682 0.3174 1.0000
8.000 1.2187 0.02364 0.01577 -0.0666 0.2976 1.0000
8.250 1.2368 0.02391 0.01615 -0.0647 0.2757 1.0000
8.500 1.2536 0.02420 0.01645 -0.0628 0.2519 1.0000
8.750 1.2675 0.02463 0.01700 -0.0605 0.2243 1.0000
9.000 1.2787 0.02519 0.01765 -0.0580 0.1898 1.0000
9.250 1.2866 0.02626 0.01862 -0.0555 0.1482 1.0000
9.500 1.2873 0.02842 0.02047 -0.0522 0.1053 1.0000
9.750 1.2819 0.03129 0.02312 -0.0481 0.0715 1.0000
10.000 1.2762 0.03390 0.02560 -0.0442 0.0571 1.0000
10.250 1.2750 0.03606 0.02785 -0.0405 0.0492 1.0000
10.500 1.2724 0.03875 0.03042 -0.0373 0.0451 1.0000
10.750 1.2795 0.04101 0.03293 -0.0348 0.0419 1.0000
11.000 1.2879 0.04348 0.03553 -0.0328 0.0393 1.0000
11.250 1.2978 0.04618 0.03831 -0.0311 0.0374 1.0000
11.500 1.3150 0.05017 0.04242 -0.0305 0.0355 1.0000
11.750 1.3185 0.05401 0.04655 -0.0288 0.0347 1.0000
12.000 1.3125 0.05691 0.04978 -0.0267 0.0341 1.0000
12.250 1.3026 0.06009 0.05328 -0.0251 0.0334 1.0000
12.500 1.2922 0.06392 0.05741 -0.0243 0.0331 1.0000
12.750 1.2796 0.06810 0.06187 -0.0243 0.0329 1.0000
13.000 1.2643 0.07287 0.06691 -0.0252 0.0328 1.0000
13.250 1.2475 0.07817 0.07247 -0.0270 0.0328 1.0000
13.500 1.2296 0.08409 0.07861 -0.0296 0.0330 1.0000
13.750 1.2105 0.09057 0.08531 -0.0329 0.0332 1.0000
14.000 1.1910 0.09762 0.09255 -0.0368 0.0336 1.0000
14.250 1.1704 0.10523 0.10033 -0.0413 0.0340 1.0000
14.500 1.1502 0.11327 0.10851 -0.0462 0.0344 1.0000
14.750 1.1316 0.12161 0.11695 -0.0510 0.0349 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S4083 (8%) (s4083-il)