S4233-136-84 (s4233-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: S4233-136-84 (s4233-il) Reynolds number: 500,000 Max Cl/Cd: 104.55 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s4233-il-500000-n5.txt Download as CSV file: xf-s4233-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3933 0.09556 0.09328 -0.0476 0.9773 0.0095
-11.250 -0.5110 0.05562 0.05307 -0.0759 0.9499 0.0086
-11.000 -0.5546 0.04372 0.04069 -0.0876 0.9127 0.0084
-10.750 -0.5685 0.04030 0.03705 -0.0888 0.8918 0.0084
-10.500 -0.5905 0.03698 0.03345 -0.0878 0.8731 0.0084
-10.250 -0.5970 0.03538 0.03166 -0.0855 0.8603 0.0085
-10.000 -0.6027 0.03267 0.02864 -0.0838 0.8495 0.0085
-9.750 -0.5993 0.03040 0.02607 -0.0824 0.8399 0.0086
-9.500 -0.5917 0.02814 0.02350 -0.0811 0.8317 0.0086
-9.250 -0.5795 0.02624 0.02132 -0.0801 0.8239 0.0087
-9.000 -0.5642 0.02453 0.01934 -0.0792 0.8169 0.0088
-8.750 -0.5465 0.02304 0.01760 -0.0784 0.8096 0.0089
-8.500 -0.5269 0.02174 0.01607 -0.0777 0.8031 0.0090
-8.250 -0.5059 0.02057 0.01471 -0.0772 0.7963 0.0092
-8.000 -0.4841 0.01953 0.01346 -0.0766 0.7901 0.0093
-7.750 -0.4611 0.01859 0.01237 -0.0761 0.7834 0.0095
-7.500 -0.4377 0.01777 0.01139 -0.0757 0.7771 0.0097
-7.250 -0.4135 0.01703 0.01053 -0.0753 0.7711 0.0099
-7.000 -0.3890 0.01639 0.00977 -0.0750 0.7646 0.0101
-6.750 -0.3640 0.01584 0.00909 -0.0747 0.7588 0.0102
-6.500 -0.3402 0.01498 0.00817 -0.0743 0.7525 0.0104
-6.250 -0.3161 0.01428 0.00739 -0.0740 0.7464 0.0107
-6.000 -0.2908 0.01374 0.00679 -0.0738 0.7405 0.0110
-5.750 -0.2649 0.01329 0.00629 -0.0736 0.7344 0.0114
-5.500 -0.2388 0.01292 0.00584 -0.0735 0.7288 0.0120
-5.250 -0.2123 0.01253 0.00540 -0.0734 0.7227 0.0125
-5.000 -0.1857 0.01216 0.00495 -0.0733 0.7167 0.0129
-4.750 -0.1589 0.01184 0.00455 -0.0732 0.7113 0.0133
-4.500 -0.1318 0.01152 0.00418 -0.0732 0.7052 0.0137
-4.250 -0.1048 0.01121 0.00379 -0.0731 0.6996 0.0145
-4.000 -0.0773 0.01097 0.00350 -0.0731 0.6940 0.0154
-3.750 -0.0497 0.01076 0.00323 -0.0731 0.6880 0.0167
-3.500 -0.0222 0.01057 0.00299 -0.0731 0.6827 0.0194
-3.250 0.0049 0.01020 0.00273 -0.0731 0.6769 0.0428
-3.000 0.0314 0.00977 0.00249 -0.0732 0.6711 0.0983
-2.750 0.0582 0.00940 0.00231 -0.0732 0.6658 0.1552
-2.500 0.0852 0.00905 0.00216 -0.0734 0.6599 0.2176
-2.250 0.1122 0.00874 0.00204 -0.0734 0.6544 0.2826
-2.000 0.1386 0.00832 0.00194 -0.0735 0.6490 0.3791
-1.750 0.1656 0.00805 0.00189 -0.0736 0.6432 0.4508
-1.500 0.1930 0.00792 0.00185 -0.0736 0.6377 0.4983
-1.250 0.2210 0.00783 0.00184 -0.0736 0.6321 0.5323
-1.000 0.2490 0.00778 0.00182 -0.0737 0.6263 0.5597
-0.750 0.2770 0.00776 0.00181 -0.0737 0.6209 0.5828
-0.500 0.3051 0.00773 0.00182 -0.0738 0.6150 0.6038
-0.250 0.3332 0.00773 0.00182 -0.0738 0.6091 0.6225
0.000 0.3613 0.00774 0.00183 -0.0739 0.6036 0.6388
0.250 0.3895 0.00774 0.00185 -0.0740 0.5975 0.6535
0.750 0.4455 0.00778 0.00190 -0.0741 0.5856 0.6818
1.000 0.4734 0.00781 0.00193 -0.0741 0.5794 0.6963
1.250 0.5012 0.00784 0.00198 -0.0742 0.5734 0.7107
1.750 0.5565 0.00791 0.00208 -0.0741 0.5604 0.7387
2.000 0.5842 0.00793 0.00215 -0.0741 0.5536 0.7527
2.250 0.6113 0.00798 0.00222 -0.0740 0.5467 0.7674
2.500 0.6387 0.00801 0.00229 -0.0740 0.5396 0.7827
2.750 0.6654 0.00807 0.00238 -0.0738 0.5323 0.7992
3.000 0.6922 0.00811 0.00247 -0.0736 0.5248 0.8170
3.250 0.7182 0.00817 0.00257 -0.0732 0.5170 0.8365
3.500 0.7440 0.00820 0.00268 -0.0728 0.5091 0.8584
4.000 0.7939 0.00830 0.00290 -0.0716 0.4926 0.9149
4.250 0.8243 0.00839 0.00302 -0.0721 0.4837 0.9507
4.500 0.8619 0.00851 0.00314 -0.0745 0.4731 0.9915
4.750 0.8894 0.00867 0.00328 -0.0746 0.4631 1.0000
5.000 0.9151 0.00886 0.00343 -0.0744 0.4527 1.0000
5.250 0.9405 0.00906 0.00361 -0.0741 0.4414 1.0000
5.500 0.9661 0.00925 0.00379 -0.0739 0.4294 1.0000
5.750 0.9911 0.00948 0.00399 -0.0736 0.4165 1.0000
6.000 1.0155 0.00974 0.00422 -0.0732 0.4016 1.0000
6.250 1.0390 0.01004 0.00446 -0.0726 0.3844 1.0000
6.750 1.0843 0.01074 0.00504 -0.0713 0.3461 1.0000
7.000 1.1035 0.01127 0.00542 -0.0702 0.3150 1.0000
7.250 1.1202 0.01193 0.00589 -0.0687 0.2783 1.0000
7.500 1.1377 0.01253 0.00635 -0.0673 0.2497 1.0000
7.750 1.1547 0.01312 0.00683 -0.0658 0.2237 1.0000
8.000 1.1678 0.01388 0.00743 -0.0638 0.1918 1.0000
8.250 1.1777 0.01467 0.00805 -0.0613 0.1613 1.0000
8.500 1.1855 0.01547 0.00872 -0.0584 0.1360 1.0000
8.750 1.1922 0.01638 0.00949 -0.0555 0.1107 1.0000
9.000 1.1993 0.01733 0.01033 -0.0529 0.0889 1.0000
9.250 1.2065 0.01834 0.01125 -0.0505 0.0709 1.0000
9.500 1.2151 0.01932 0.01218 -0.0484 0.0567 1.0000
9.750 1.2232 0.02039 0.01319 -0.0464 0.0444 1.0000
10.000 1.2321 0.02146 0.01424 -0.0447 0.0355 1.0000
10.250 1.2389 0.02273 0.01547 -0.0428 0.0260 1.0000
10.500 1.2459 0.02403 0.01676 -0.0411 0.0180 1.0000
10.750 1.2527 0.02542 0.01815 -0.0395 0.0133 1.0000
11.000 1.2609 0.02675 0.01951 -0.0382 0.0112 1.0000
11.250 1.2694 0.02811 0.02092 -0.0370 0.0101 1.0000
11.500 1.2784 0.02946 0.02234 -0.0359 0.0094 1.0000
11.750 1.2868 0.03090 0.02384 -0.0349 0.0090 1.0000
12.000 1.2937 0.03251 0.02552 -0.0339 0.0085 1.0000
12.250 1.3004 0.03419 0.02727 -0.0329 0.0082 1.0000
12.500 1.3046 0.03613 0.02929 -0.0320 0.0078 1.0000
12.750 1.3108 0.03795 0.03120 -0.0313 0.0077 1.0000
13.000 1.3163 0.03989 0.03322 -0.0306 0.0076 1.0000
13.250 1.3206 0.04200 0.03542 -0.0300 0.0073 1.0000
13.500 1.3248 0.04419 0.03770 -0.0296 0.0071 1.0000
13.750 1.3283 0.04653 0.04012 -0.0293 0.0071 1.0000
14.000 1.3306 0.04906 0.04275 -0.0290 0.0069 1.0000
14.250 1.3324 0.05171 0.04550 -0.0289 0.0067 1.0000
14.500 1.3333 0.05457 0.04845 -0.0289 0.0066 1.0000
14.750 1.3342 0.05752 0.05149 -0.0291 0.0065 1.0000
15.000 1.3335 0.06070 0.05478 -0.0294 0.0064 1.0000
15.250 1.3335 0.06392 0.05808 -0.0298 0.0063 1.0000
15.500 1.3309 0.06756 0.06182 -0.0304 0.0062 1.0000
15.750 1.3281 0.07132 0.06568 -0.0311 0.0061 1.0000
16.000 1.3246 0.07527 0.06972 -0.0320 0.0060 1.0000
16.250 1.3190 0.07962 0.07417 -0.0332 0.0058 1.0000
16.500 1.3135 0.08406 0.07871 -0.0344 0.0058 1.0000
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Polar data table (+)
Polar graphs
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