S4083 (8%) (s4083-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: S4083 (8%) (s4083-il) Reynolds number: 100,000 Max Cl/Cd: 56.2 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4083-il-100000-n5.txt Download as CSV file: xf-s4083-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3920 0.10386 0.09900 -0.0229 1.0000 0.0426
-8.000 -0.3924 0.10105 0.09627 -0.0239 1.0000 0.0427
-7.750 -0.3927 0.09806 0.09335 -0.0251 1.0000 0.0427
-7.500 -0.3891 0.09438 0.08976 -0.0274 1.0000 0.0428
-7.250 -0.3835 0.08949 0.08489 -0.0230 1.0000 0.0439
-7.000 -0.3780 0.08630 0.08172 -0.0226 1.0000 0.0445
-6.750 -0.3724 0.08338 0.07885 -0.0222 1.0000 0.0456
-6.500 -0.3669 0.08058 0.07610 -0.0225 1.0000 0.0477
-6.250 -0.3614 0.07743 0.07300 -0.0244 1.0000 0.0502
-6.000 -0.3533 0.07373 0.06934 -0.0285 1.0000 0.0527
-5.750 -0.3314 0.06819 0.06358 -0.0423 1.0000 0.0554
-5.500 -0.3229 0.06337 0.05880 -0.0432 1.0000 0.0562
-5.000 -0.2937 0.05209 0.04738 -0.0448 1.0000 0.0295
-4.750 -0.2772 0.04805 0.04323 -0.0465 1.0000 0.0282
-4.500 -0.2563 0.04336 0.03833 -0.0490 1.0000 0.0268
-4.250 -0.2323 0.03840 0.03302 -0.0513 1.0000 0.0254
-4.000 -0.2061 0.03350 0.02761 -0.0532 1.0000 0.0241
-3.750 -0.1773 0.02921 0.02262 -0.0544 0.9996 0.0231
-3.500 -0.1348 0.02586 0.01862 -0.0579 0.9934 0.0228
-3.250 -0.0940 0.02330 0.01551 -0.0607 0.9860 0.0229
-3.000 -0.0554 0.02127 0.01310 -0.0628 0.9766 0.0234
-2.750 -0.0180 0.01965 0.01121 -0.0645 0.9658 0.0246
-2.500 0.0188 0.01851 0.00989 -0.0661 0.9532 0.0281
-2.250 0.0550 0.01737 0.00856 -0.0674 0.9392 0.0316
-2.000 0.0908 0.01618 0.00733 -0.0687 0.9238 0.0359
-1.750 0.1293 0.01521 0.00627 -0.0705 0.9068 0.0492
-1.500 0.1679 0.01403 0.00549 -0.0726 0.8862 0.1340
-1.250 0.2083 0.01280 0.00509 -0.0753 0.8630 0.3873
-1.000 0.2449 0.01180 0.00486 -0.0764 0.8345 0.6654
-0.750 0.3009 0.01105 0.00433 -0.0809 0.7994 1.0000
-0.500 0.3388 0.01116 0.00400 -0.0825 0.7613 1.0000
-0.250 0.3717 0.01134 0.00380 -0.0832 0.7255 1.0000
0.000 0.4018 0.01155 0.00367 -0.0833 0.6939 1.0000
0.500 0.4580 0.01201 0.00357 -0.0829 0.6410 1.0000
0.750 0.4851 0.01225 0.00358 -0.0826 0.6193 1.0000
1.000 0.5118 0.01249 0.00362 -0.0822 0.5996 1.0000
1.250 0.5383 0.01274 0.00368 -0.0817 0.5821 1.0000
1.500 0.5646 0.01299 0.00376 -0.0813 0.5660 1.0000
1.750 0.5908 0.01325 0.00388 -0.0808 0.5511 1.0000
2.000 0.6169 0.01350 0.00403 -0.0804 0.5372 1.0000
2.250 0.6429 0.01376 0.00419 -0.0799 0.5239 1.0000
2.500 0.6689 0.01402 0.00437 -0.0794 0.5114 1.0000
2.750 0.6948 0.01428 0.00457 -0.0790 0.4994 1.0000
3.000 0.7206 0.01456 0.00483 -0.0785 0.4881 1.0000
3.250 0.7463 0.01485 0.00505 -0.0780 0.4772 1.0000
3.500 0.7719 0.01515 0.00530 -0.0775 0.4663 1.0000
3.750 0.7974 0.01543 0.00559 -0.0770 0.4550 1.0000
4.000 0.8228 0.01572 0.00589 -0.0764 0.4442 1.0000
4.250 0.8481 0.01604 0.00623 -0.0759 0.4342 1.0000
4.500 0.8733 0.01635 0.00655 -0.0753 0.4239 1.0000
4.750 0.8984 0.01666 0.00693 -0.0747 0.4133 1.0000
5.000 0.9233 0.01699 0.00730 -0.0742 0.4029 1.0000
5.250 0.9480 0.01733 0.00771 -0.0735 0.3928 1.0000
5.500 0.9725 0.01766 0.00811 -0.0728 0.3817 1.0000
5.750 0.9968 0.01799 0.00855 -0.0721 0.3701 1.0000
6.000 1.0208 0.01834 0.00899 -0.0714 0.3584 1.0000
6.250 1.0446 0.01870 0.00948 -0.0706 0.3467 1.0000
6.500 1.0681 0.01907 0.00995 -0.0698 0.3344 1.0000
6.750 1.0911 0.01944 0.01043 -0.0689 0.3212 1.0000
7.000 1.1138 0.01982 0.01094 -0.0680 0.3066 1.0000
7.250 1.1361 0.02022 0.01148 -0.0670 0.2913 1.0000
7.500 1.1579 0.02066 0.01209 -0.0660 0.2752 1.0000
7.750 1.1790 0.02114 0.01269 -0.0648 0.2582 1.0000
8.000 1.1992 0.02169 0.01333 -0.0636 0.2392 1.0000
8.250 1.2188 0.02230 0.01405 -0.0623 0.2171 1.0000
8.500 1.2366 0.02305 0.01484 -0.0609 0.1910 1.0000
8.750 1.2514 0.02407 0.01575 -0.0592 0.1573 1.0000
9.000 1.2634 0.02544 0.01696 -0.0575 0.1171 1.0000
9.250 1.2724 0.02716 0.01842 -0.0554 0.0771 1.0000
9.500 1.2798 0.02899 0.02009 -0.0531 0.0496 1.0000
9.750 1.2846 0.03095 0.02202 -0.0504 0.0332 1.0000
10.000 1.2864 0.03303 0.02414 -0.0475 0.0261 1.0000
10.250 1.2872 0.03488 0.02618 -0.0443 0.0226 1.0000
10.500 1.2835 0.03694 0.02838 -0.0410 0.0206 1.0000
10.750 1.2763 0.03932 0.03091 -0.0379 0.0195 1.0000
11.000 1.2711 0.04173 0.03350 -0.0356 0.0188 1.0000
11.250 1.2649 0.04450 0.03649 -0.0341 0.0181 1.0000
11.500 1.2584 0.04764 0.03983 -0.0333 0.0176 1.0000
11.750 1.2516 0.05117 0.04354 -0.0332 0.0171 1.0000
12.000 1.2451 0.05496 0.04752 -0.0337 0.0167 1.0000
12.250 1.2388 0.05899 0.05172 -0.0344 0.0164 1.0000
12.500 1.2330 0.06311 0.05601 -0.0353 0.0160 1.0000
12.750 1.2278 0.06729 0.06040 -0.0364 0.0157 1.0000
13.000 1.2210 0.07183 0.06510 -0.0379 0.0151 1.0000
13.250 1.2149 0.07638 0.06980 -0.0393 0.0148 1.0000
13.500 1.2090 0.08095 0.07452 -0.0408 0.0146 1.0000
13.750 1.2008 0.08604 0.07974 -0.0429 0.0141 1.0000
14.000 1.1932 0.09113 0.08497 -0.0449 0.0139 1.0000
14.250 1.1851 0.09643 0.09040 -0.0472 0.0136 1.0000
14.500 1.1769 0.10192 0.09603 -0.0495 0.0134 1.0000
14.750 1.1685 0.10766 0.10192 -0.0520 0.0132 1.0000
15.000 1.1586 0.11393 0.10833 -0.0551 0.0130 1.0000
15.250 1.1488 0.12056 0.11514 -0.0587 0.0129 1.0000
15.500 1.1389 0.12746 0.12220 -0.0625 0.0129 1.0000
15.750 1.1281 0.13484 0.12974 -0.0668 0.0129 1.0000
16.000 1.1171 0.14259 0.13764 -0.0713 0.0130 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S4083 (8%) (s4083-il)