S4233-136-84 (s4233-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4233-136-84 (s4233-il) Reynolds number: 100,000 Max Cl/Cd: 54.29 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4233-il-100000-n5.txt Download as CSV file: xf-s4233-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S4233-136-84
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3685 0.09129 0.08646 -0.0540 1.0000 0.0267
-10.250 -0.3717 0.08687 0.08210 -0.0559 1.0000 0.0264
-10.000 -0.3825 0.08079 0.07610 -0.0589 1.0000 0.0263
-9.750 -0.3980 0.07441 0.06980 -0.0620 1.0000 0.0260
-9.500 -0.4201 0.07005 0.06555 -0.0628 1.0000 0.0251
-9.250 -0.4382 0.05915 0.05440 -0.0776 0.9785 0.0250
-9.000 -0.4462 0.05272 0.04763 -0.0851 0.9612 0.0244
-8.750 -0.4461 0.04796 0.04245 -0.0886 0.9476 0.0249
-8.500 -0.4411 0.04409 0.03816 -0.0900 0.9355 0.0250
-8.250 -0.4319 0.04071 0.03431 -0.0906 0.9252 0.0254
-8.000 -0.4191 0.03767 0.03080 -0.0906 0.9160 0.0257
-7.750 -0.4054 0.03516 0.02787 -0.0899 0.9061 0.0258
-7.500 -0.3855 0.03278 0.02507 -0.0896 0.8993 0.0259
-7.250 -0.3677 0.03088 0.02282 -0.0886 0.8899 0.0262
-7.000 -0.3440 0.02906 0.02065 -0.0883 0.8840 0.0265
-6.750 -0.3233 0.02763 0.01896 -0.0873 0.8753 0.0270
-6.500 -0.2994 0.02621 0.01740 -0.0868 0.8694 0.0276
-6.250 -0.2783 0.02512 0.01625 -0.0860 0.8612 0.0283
-6.000 -0.2550 0.02417 0.01520 -0.0854 0.8549 0.0297
-5.750 -0.2327 0.02338 0.01430 -0.0847 0.8476 0.0320
-5.500 -0.2099 0.02256 0.01335 -0.0839 0.8409 0.0339
-5.250 -0.1877 0.02172 0.01245 -0.0831 0.8346 0.0360
-5.000 -0.1654 0.02104 0.01167 -0.0823 0.8272 0.0388
-4.750 -0.1412 0.02029 0.01077 -0.0816 0.8221 0.0430
-4.500 -0.1190 0.01966 0.01011 -0.0809 0.8142 0.0522
-4.250 -0.0964 0.01868 0.00937 -0.0802 0.8084 0.0928
-4.000 -0.0745 0.01784 0.00889 -0.0797 0.8019 0.1756
-3.750 -0.0542 0.01692 0.00863 -0.0790 0.7952 0.3102
-3.500 -0.0319 0.01630 0.00850 -0.0780 0.7906 0.4315
-3.250 -0.0097 0.01615 0.00852 -0.0769 0.7828 0.4972
-3.000 0.0157 0.01602 0.00838 -0.0761 0.7774 0.5433
-2.750 0.0406 0.01598 0.00831 -0.0753 0.7713 0.5810
-2.500 0.0655 0.01595 0.00825 -0.0745 0.7648 0.6137
-2.250 0.0920 0.01588 0.00809 -0.0737 0.7602 0.6430
-2.000 0.1159 0.01592 0.00812 -0.0728 0.7529 0.6682
-1.750 0.1418 0.01589 0.00801 -0.0721 0.7473 0.6929
-1.500 0.1675 0.01586 0.00793 -0.0713 0.7419 0.7139
-1.250 0.1922 0.01588 0.00792 -0.0705 0.7350 0.7344
-1.000 0.2186 0.01583 0.00777 -0.0699 0.7301 0.7547
-0.750 0.2428 0.01587 0.00780 -0.0690 0.7233 0.7737
-0.500 0.2681 0.01585 0.00774 -0.0682 0.7174 0.7926
-0.250 0.2943 0.01581 0.00764 -0.0675 0.7125 0.8118
0.000 0.3181 0.01587 0.00770 -0.0666 0.7052 0.8316
0.250 0.3449 0.01581 0.00760 -0.0660 0.7000 0.8514
0.500 0.3709 0.01585 0.00763 -0.0655 0.6934 0.8715
0.750 0.3997 0.01585 0.00761 -0.0655 0.6872 0.8929
1.000 0.4333 0.01579 0.00749 -0.0663 0.6823 0.9142
1.250 0.4684 0.01588 0.00759 -0.0680 0.6745 0.9364
1.500 0.5084 0.01584 0.00749 -0.0704 0.6691 0.9577
1.750 0.5492 0.01592 0.00755 -0.0734 0.6618 0.9804
2.000 0.5863 0.01595 0.00753 -0.0756 0.6554 1.0000
2.250 0.6073 0.01609 0.00761 -0.0747 0.6487 1.0000
2.500 0.6297 0.01624 0.00772 -0.0741 0.6416 1.0000
2.750 0.6552 0.01633 0.00776 -0.0737 0.6357 1.0000
3.000 0.6780 0.01656 0.00798 -0.0731 0.6277 1.0000
3.250 0.7053 0.01661 0.00797 -0.0730 0.6220 1.0000
3.500 0.7277 0.01689 0.00828 -0.0724 0.6133 1.0000
3.750 0.7551 0.01696 0.00832 -0.0722 0.6072 1.0000
4.000 0.7779 0.01724 0.00865 -0.0717 0.5985 1.0000
4.250 0.8053 0.01732 0.00870 -0.0715 0.5920 1.0000
4.500 0.8281 0.01761 0.00907 -0.0709 0.5830 1.0000
4.750 0.8556 0.01770 0.00913 -0.0708 0.5763 1.0000
5.000 0.8779 0.01800 0.00953 -0.0701 0.5667 1.0000
5.250 0.9039 0.01816 0.00971 -0.0698 0.5590 1.0000
5.500 0.9275 0.01841 0.01003 -0.0692 0.5497 1.0000
5.750 0.9516 0.01865 0.01033 -0.0687 0.5408 1.0000
6.000 0.9769 0.01882 0.01053 -0.0683 0.5320 1.0000
6.250 0.9990 0.01913 0.01096 -0.0675 0.5216 1.0000
6.500 1.0229 0.01937 0.01125 -0.0669 0.5119 1.0000
6.750 1.0470 0.01958 0.01151 -0.0663 0.5016 1.0000
7.000 1.0680 0.01991 0.01196 -0.0653 0.4897 1.0000
7.250 1.0895 0.02021 0.01235 -0.0644 0.4777 1.0000
7.500 1.1106 0.02051 0.01272 -0.0634 0.4650 1.0000
7.750 1.1309 0.02083 0.01310 -0.0622 0.4513 1.0000
8.000 1.1495 0.02119 0.01354 -0.0609 0.4361 1.0000
8.250 1.1667 0.02160 0.01400 -0.0593 0.4199 1.0000
8.500 1.1825 0.02206 0.01452 -0.0576 0.4031 1.0000
8.750 1.1969 0.02258 0.01507 -0.0557 0.3858 1.0000
9.000 1.2089 0.02317 0.01568 -0.0536 0.3677 1.0000
9.250 1.2167 0.02386 0.01640 -0.0508 0.3487 1.0000
9.500 1.2225 0.02470 0.01725 -0.0480 0.3281 1.0000
9.750 1.2271 0.02568 0.01820 -0.0453 0.3073 1.0000
10.000 1.2311 0.02684 0.01935 -0.0429 0.2852 1.0000
10.250 1.2324 0.02822 0.02068 -0.0404 0.2623 1.0000
10.500 1.2313 0.02989 0.02226 -0.0380 0.2361 1.0000
10.750 1.2275 0.03189 0.02414 -0.0358 0.2079 1.0000
11.000 1.2217 0.03424 0.02634 -0.0338 0.1789 1.0000
11.250 1.2153 0.03682 0.02876 -0.0321 0.1513 1.0000
11.500 1.2090 0.03958 0.03137 -0.0307 0.1261 1.0000
11.750 1.2044 0.04235 0.03404 -0.0297 0.1063 1.0000
12.000 1.2009 0.04514 0.03679 -0.0288 0.0900 1.0000
12.250 1.1977 0.04802 0.03966 -0.0281 0.0769 1.0000
12.500 1.1936 0.05110 0.04274 -0.0276 0.0651 1.0000
12.750 1.1896 0.05432 0.04597 -0.0273 0.0554 1.0000
13.000 1.1848 0.05775 0.04944 -0.0272 0.0482 1.0000
13.250 1.1788 0.06146 0.05318 -0.0273 0.0427 1.0000
13.500 1.1750 0.06505 0.05688 -0.0275 0.0387 1.0000
13.750 1.1699 0.06892 0.06085 -0.0279 0.0356 1.0000
14.000 1.1637 0.07305 0.06504 -0.0285 0.0332 1.0000
14.250 1.1609 0.07683 0.06897 -0.0292 0.0306 1.0000
14.500 1.1570 0.08086 0.07309 -0.0300 0.0287 1.0000
14.750 1.1523 0.08507 0.07739 -0.0311 0.0275 1.0000
15.000 1.1503 0.08895 0.08138 -0.0320 0.0260 1.0000
15.250 1.1499 0.09264 0.08522 -0.0328 0.0249 1.0000
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Polar data table (+)
Polar graphs
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