S4233-136-84 (s4233-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S4233-136-84 (s4233-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.02 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s4233-il-1000000.txt Download as CSV file: xf-s4233-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2840 0.08372 0.08193 -0.0521 0.8794 0.0151
-10.750 -0.2889 0.07811 0.07631 -0.0544 0.8727 0.0153
-10.500 -0.2989 0.07119 0.06936 -0.0574 0.8672 0.0155
-10.250 -0.3180 0.06186 0.06005 -0.0617 0.8619 0.0157
-10.000 -0.5512 0.04034 0.03762 -0.0868 0.8686 0.0144
-9.750 -0.5566 0.03773 0.03481 -0.0853 0.8572 0.0144
-9.500 -0.5489 0.03591 0.03290 -0.0845 0.8485 0.0146
-9.250 -0.5357 0.03478 0.03171 -0.0838 0.8399 0.0149
-9.000 -0.5275 0.03274 0.02950 -0.0829 0.8318 0.0151
-8.750 -0.5156 0.03101 0.02758 -0.0821 0.8240 0.0155
-8.500 -0.5332 0.02084 0.01608 -0.0777 0.8157 0.0112
-8.250 -0.5120 0.01951 0.01453 -0.0770 0.8089 0.0111
-8.000 -0.4894 0.01835 0.01320 -0.0765 0.8026 0.0111
-7.750 -0.4666 0.01716 0.01187 -0.0761 0.7959 0.0111
-7.500 -0.4433 0.01613 0.01074 -0.0756 0.7898 0.0113
-7.250 -0.4186 0.01539 0.00993 -0.0754 0.7833 0.0117
-7.000 -0.3944 0.01454 0.00897 -0.0750 0.7770 0.0117
-6.750 -0.3694 0.01380 0.00816 -0.0747 0.7709 0.0119
-6.500 -0.3442 0.01316 0.00744 -0.0744 0.7645 0.0121
-6.250 -0.3188 0.01258 0.00679 -0.0741 0.7587 0.0124
-6.000 -0.2928 0.01206 0.00621 -0.0739 0.7523 0.0127
-5.750 -0.2668 0.01161 0.00568 -0.0737 0.7463 0.0130
-5.500 -0.2400 0.01121 0.00523 -0.0736 0.7404 0.0134
-5.250 -0.2132 0.01085 0.00480 -0.0735 0.7342 0.0137
-5.000 -0.1862 0.01054 0.00443 -0.0734 0.7285 0.0139
-4.750 -0.1598 0.01001 0.00382 -0.0733 0.7224 0.0143
-4.500 -0.1328 0.00965 0.00339 -0.0732 0.7166 0.0150
-4.250 -0.1051 0.00939 0.00310 -0.0733 0.7109 0.0159
-4.000 -0.0773 0.00917 0.00284 -0.0733 0.7049 0.0170
-3.750 -0.0495 0.00899 0.00258 -0.0733 0.6991 0.0181
-3.500 -0.0213 0.00875 0.00233 -0.0734 0.6935 0.0210
-3.250 0.0057 0.00832 0.00206 -0.0734 0.6877 0.0602
-3.000 0.0320 0.00779 0.00183 -0.0734 0.6822 0.1446
-2.750 0.0590 0.00736 0.00168 -0.0736 0.6765 0.2225
-2.500 0.0860 0.00702 0.00156 -0.0737 0.6708 0.2987
-2.250 0.1136 0.00675 0.00148 -0.0739 0.6655 0.3632
-2.000 0.1415 0.00653 0.00141 -0.0740 0.6597 0.4182
-1.750 0.1691 0.00638 0.00137 -0.0741 0.6542 0.4722
-1.500 0.1971 0.00619 0.00136 -0.0742 0.6487 0.5302
-1.250 0.2253 0.00610 0.00135 -0.0743 0.6430 0.5694
-1.000 0.2536 0.00609 0.00134 -0.0744 0.6376 0.5912
-0.750 0.2824 0.00606 0.00134 -0.0746 0.6319 0.6116
-0.500 0.3109 0.00606 0.00134 -0.0748 0.6263 0.6301
0.000 0.3681 0.00605 0.00136 -0.0751 0.6149 0.6620
0.250 0.3963 0.00607 0.00138 -0.0752 0.6092 0.6767
0.500 0.4249 0.00607 0.00140 -0.0753 0.6036 0.6906
0.750 0.4533 0.00608 0.00142 -0.0755 0.5974 0.7038
1.000 0.4816 0.00611 0.00145 -0.0756 0.5917 0.7168
1.250 0.5101 0.00611 0.00149 -0.0757 0.5855 0.7302
1.500 0.5381 0.00615 0.00153 -0.0758 0.5792 0.7444
1.750 0.5664 0.00616 0.00157 -0.0759 0.5731 0.7592
2.000 0.5943 0.00618 0.00162 -0.0760 0.5664 0.7746
2.250 0.6221 0.00621 0.00168 -0.0760 0.5601 0.7906
2.500 0.6498 0.00623 0.00174 -0.0760 0.5532 0.8076
2.750 0.6770 0.00627 0.00182 -0.0759 0.5464 0.8263
3.000 0.7043 0.00627 0.00189 -0.0758 0.5392 0.8471
3.250 0.7304 0.00632 0.00197 -0.0754 0.5319 0.8703
3.500 0.7563 0.00631 0.00205 -0.0750 0.5244 0.8977
3.750 0.7804 0.00635 0.00214 -0.0741 0.5167 0.9318
4.000 0.8119 0.00637 0.00221 -0.0749 0.5081 0.9688
4.250 0.8519 0.00647 0.00229 -0.0777 0.4985 1.0000
4.500 0.8786 0.00661 0.00239 -0.0777 0.4889 1.0000
4.750 0.9056 0.00673 0.00250 -0.0777 0.4792 1.0000
5.000 0.9323 0.00688 0.00262 -0.0776 0.4687 1.0000
5.250 0.9585 0.00706 0.00276 -0.0775 0.4570 1.0000
5.500 0.9847 0.00724 0.00290 -0.0774 0.4437 1.0000
5.750 1.0106 0.00743 0.00305 -0.0772 0.4294 1.0000
6.000 1.0366 0.00763 0.00322 -0.0770 0.4164 1.0000
6.250 1.0612 0.00791 0.00343 -0.0767 0.3972 1.0000
6.500 1.0853 0.00822 0.00365 -0.0762 0.3737 1.0000
6.750 1.1086 0.00858 0.00391 -0.0757 0.3502 1.0000
7.000 1.1311 0.00898 0.00420 -0.0750 0.3252 1.0000
7.250 1.1536 0.00937 0.00449 -0.0744 0.3015 1.0000
7.500 1.1746 0.00984 0.00484 -0.0735 0.2758 1.0000
7.750 1.1944 0.01037 0.00524 -0.0724 0.2481 1.0000
8.000 1.2120 0.01099 0.00570 -0.0710 0.2156 1.0000
8.250 1.2275 0.01170 0.00622 -0.0693 0.1826 1.0000
8.500 1.2405 0.01249 0.00682 -0.0672 0.1495 1.0000
8.750 1.2522 0.01325 0.00743 -0.0649 0.1211 1.0000
9.000 1.2589 0.01402 0.00806 -0.0617 0.0972 1.0000
9.250 1.2647 0.01485 0.00877 -0.0584 0.0763 1.0000
9.500 1.2725 0.01566 0.00950 -0.0557 0.0600 1.0000
9.750 1.2778 0.01667 0.01040 -0.0529 0.0433 1.0000
10.000 1.2837 0.01771 0.01137 -0.0503 0.0298 1.0000
10.250 1.2861 0.01904 0.01261 -0.0475 0.0164 1.0000
10.500 1.2943 0.02011 0.01368 -0.0455 0.0126 1.0000
10.750 1.3044 0.02112 0.01472 -0.0438 0.0114 1.0000
11.000 1.3128 0.02228 0.01592 -0.0421 0.0102 1.0000
11.250 1.3239 0.02330 0.01700 -0.0408 0.0099 1.0000
11.500 1.3332 0.02448 0.01824 -0.0393 0.0094 1.0000
11.750 1.3420 0.02573 0.01955 -0.0380 0.0091 1.0000
12.000 1.3496 0.02713 0.02100 -0.0367 0.0087 1.0000
12.250 1.3571 0.02858 0.02251 -0.0355 0.0085 1.0000
12.500 1.3604 0.03042 0.02443 -0.0342 0.0081 1.0000
12.750 1.3604 0.03262 0.02672 -0.0328 0.0078 1.0000
13.000 1.3642 0.03456 0.02874 -0.0318 0.0078 1.0000
13.250 1.3702 0.03635 0.03060 -0.0310 0.0076 1.0000
13.500 1.3758 0.03825 0.03257 -0.0303 0.0075 1.0000
13.750 1.3818 0.04017 0.03455 -0.0298 0.0072 1.0000
14.000 1.3839 0.04253 0.03700 -0.0292 0.0071 1.0000
14.250 1.3862 0.04497 0.03952 -0.0288 0.0070 1.0000
14.500 1.3863 0.04772 0.04236 -0.0285 0.0069 1.0000
14.750 1.3883 0.05034 0.04506 -0.0284 0.0068 1.0000
15.000 1.3896 0.05309 0.04789 -0.0284 0.0067 1.0000
15.250 1.3890 0.05619 0.05107 -0.0285 0.0066 1.0000
15.500 1.3867 0.05958 0.05455 -0.0288 0.0065 1.0000
15.750 1.3853 0.06293 0.05798 -0.0292 0.0064 1.0000
16.000 1.3838 0.06639 0.06154 -0.0298 0.0065 1.0000
16.250 1.3783 0.07049 0.06570 -0.0306 0.0062 1.0000
16.500 1.3759 0.07425 0.06956 -0.0314 0.0062 1.0000
16.750 1.3714 0.07839 0.07380 -0.0325 0.0062 1.0000
17.000 1.3652 0.08288 0.07838 -0.0337 0.0061 1.0000
17.250 1.3600 0.08731 0.08290 -0.0350 0.0060 1.0000
17.500 1.3516 0.09222 0.08791 -0.0365 0.0059 1.0000
17.750 1.3454 0.09690 0.09268 -0.0381 0.0059 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S4233-136-84 (s4233-il)