Rhode St. Genese 36 (rhodesg36-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Rhode St. Genese 36 (rhodesg36-il) Reynolds number: 200,000 Max Cl/Cd: 54.02 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rhodesg36-il-200000.txt Download as CSV file: xf-rhodesg36-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: Rhode St. Genese 36
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 0.0446 0.09621 0.09263 -0.0927 0.9592 0.0751
-12.500 0.0529 0.09266 0.08907 -0.0954 0.9535 0.0778
-12.250 0.0405 0.08721 0.08362 -0.1016 0.9490 0.0801
-12.000 0.0720 0.08401 0.08041 -0.1024 0.9466 0.0812
-11.750 0.0828 0.08164 0.07804 -0.1020 0.9374 0.0826
-11.500 0.0886 0.07881 0.07522 -0.1026 0.9292 0.0847
-11.250 0.0486 0.07341 0.06984 -0.1083 0.9172 0.0885
-11.000 0.0708 0.07124 0.06767 -0.1058 0.9100 0.0892
-10.750 0.0838 0.06926 0.06570 -0.1041 0.9009 0.0903
-10.500 0.0924 0.06681 0.06325 -0.1035 0.8938 0.0922
-10.250 0.0495 0.07247 0.06875 -0.1111 0.9109 0.0920
-10.000 0.0461 0.06986 0.06616 -0.1115 0.8983 0.0947
-9.750 -0.0119 0.06340 0.05964 -0.1174 0.8793 0.0983
-9.500 0.0078 0.06229 0.05858 -0.1145 0.8713 0.0993
-9.250 0.0229 0.06056 0.05683 -0.1132 0.8648 0.1011
-9.000 -0.0119 0.05487 0.05085 -0.1174 0.8508 0.1085
-8.750 0.0138 0.05346 0.04949 -0.1158 0.8463 0.1098
-8.500 -0.0028 0.05030 0.04590 -0.1167 0.8336 0.1192
-8.250 0.0224 0.04813 0.04383 -0.1158 0.8279 0.1204
-8.000 -0.0294 0.03124 0.02510 -0.1133 0.8169 0.0801
-7.750 -0.0059 0.02907 0.02274 -0.1126 0.8114 0.0784
-7.500 0.0098 0.02721 0.02061 -0.1109 0.8018 0.0781
-7.250 0.0311 0.02542 0.01845 -0.1098 0.7951 0.0782
-7.000 0.0522 0.02402 0.01674 -0.1085 0.7879 0.0784
-6.750 0.0747 0.02282 0.01527 -0.1073 0.7797 0.0786
-6.500 0.1012 0.02179 0.01390 -0.1066 0.7735 0.0792
-6.250 0.1230 0.02083 0.01281 -0.1054 0.7646 0.0801
-6.000 0.1495 0.01981 0.01177 -0.1049 0.7569 0.0820
-5.750 0.1748 0.01919 0.01109 -0.1042 0.7490 0.0840
-5.500 0.2002 0.01856 0.01037 -0.1034 0.7406 0.0857
-5.250 0.2282 0.01794 0.00960 -0.1029 0.7337 0.0873
-5.000 0.2516 0.01732 0.00897 -0.1019 0.7242 0.0891
-4.750 0.2786 0.01671 0.00838 -0.1014 0.7166 0.0921
-4.500 0.3022 0.01633 0.00802 -0.1003 0.7067 0.0951
-4.250 0.3288 0.01588 0.00747 -0.0996 0.6978 0.0978
-4.000 0.3512 0.01547 0.00716 -0.0984 0.6865 0.1014
-3.750 0.3768 0.01517 0.00680 -0.0976 0.6753 0.1062
-3.500 0.4004 0.01489 0.00654 -0.0965 0.6618 0.1116
-3.250 0.4237 0.01471 0.00633 -0.0953 0.6465 0.1187
-3.000 0.4468 0.01458 0.00618 -0.0940 0.6291 0.1293
-2.750 0.4687 0.01446 0.00604 -0.0926 0.6090 0.1468
-2.500 0.4885 0.01429 0.00585 -0.0908 0.5847 0.1763
-2.250 0.5049 0.01414 0.00573 -0.0886 0.5520 0.2091
-2.000 0.5193 0.01413 0.00565 -0.0860 0.5112 0.2407
-1.750 0.5321 0.01422 0.00565 -0.0832 0.4778 0.2823
-1.500 0.5442 0.01415 0.00575 -0.0805 0.4576 0.3838
-1.250 0.6027 0.01346 0.00644 -0.0860 0.4385 0.9284
-1.000 0.6995 0.01424 0.00685 -0.1000 0.4215 1.0000
-0.750 0.7174 0.01457 0.00699 -0.0983 0.4148 1.0000
-0.500 0.7360 0.01482 0.00714 -0.0967 0.4088 1.0000
-0.250 0.7556 0.01511 0.00729 -0.0952 0.4035 1.0000
0.000 0.7784 0.01552 0.00749 -0.0944 0.3985 1.0000
0.250 0.7990 0.01577 0.00769 -0.0932 0.3945 1.0000
0.500 0.8197 0.01603 0.00789 -0.0920 0.3905 1.0000
0.750 0.8413 0.01632 0.00810 -0.0909 0.3866 1.0000
1.000 0.8642 0.01666 0.00833 -0.0902 0.3831 1.0000
1.250 0.8918 0.01714 0.00864 -0.0903 0.3793 1.0000
1.500 0.9128 0.01742 0.00891 -0.0892 0.3763 1.0000
1.750 0.9337 0.01770 0.00919 -0.0881 0.3733 1.0000
2.000 0.9559 0.01801 0.00947 -0.0872 0.3703 1.0000
2.250 0.9792 0.01835 0.00976 -0.0866 0.3675 1.0000
2.500 1.0035 0.01871 0.01007 -0.0862 0.3649 1.0000
2.750 1.0298 0.01915 0.01042 -0.0862 0.3625 1.0000
3.000 1.0616 0.01980 0.01095 -0.0873 0.3598 1.0000
3.250 1.0822 0.02013 0.01133 -0.0863 0.3581 1.0000
3.500 1.1034 0.02049 0.01173 -0.0854 0.3562 1.0000
3.750 1.1254 0.02088 0.01215 -0.0846 0.3541 1.0000
4.000 1.1476 0.02128 0.01257 -0.0840 0.3519 1.0000
4.250 1.1704 0.02169 0.01298 -0.0834 0.3496 1.0000
4.500 1.1943 0.02211 0.01340 -0.0831 0.3475 1.0000
4.750 1.2196 0.02258 0.01385 -0.0831 0.3456 1.0000
5.000 1.2467 0.02312 0.01435 -0.0834 0.3438 1.0000
5.250 1.2757 0.02384 0.01503 -0.0842 0.3421 1.0000
5.500 1.3011 0.02460 0.01583 -0.0844 0.3405 1.0000
5.750 1.3203 0.02508 0.01640 -0.0834 0.3392 1.0000
6.000 1.3393 0.02559 0.01701 -0.0823 0.3377 1.0000
6.250 1.3580 0.02612 0.01762 -0.0813 0.3359 1.0000
6.500 1.3764 0.02665 0.01823 -0.0802 0.3339 1.0000
6.750 1.3947 0.02716 0.01880 -0.0791 0.3317 1.0000
7.000 1.4141 0.02756 0.01922 -0.0783 0.3290 1.0000
7.250 1.4375 0.02799 0.01964 -0.0781 0.3266 1.0000
7.500 1.4671 0.02861 0.02018 -0.0791 0.3239 1.0000
7.750 1.4872 0.02946 0.02108 -0.0786 0.3217 1.0000
8.000 1.4963 0.02994 0.02171 -0.0761 0.3197 1.0000
8.250 1.5074 0.03052 0.02242 -0.0740 0.3177 1.0000
8.500 1.5200 0.03114 0.02313 -0.0722 0.3156 1.0000
8.750 1.5314 0.03172 0.02380 -0.0702 0.3135 1.0000
9.000 1.5442 0.03225 0.02439 -0.0684 0.3114 1.0000
9.250 1.5620 0.03271 0.02489 -0.0675 0.3093 1.0000
9.500 1.5893 0.03313 0.02527 -0.0682 0.3070 1.0000
9.750 1.6224 0.03406 0.02617 -0.0702 0.3043 1.0000
10.000 1.6154 0.03475 0.02704 -0.0654 0.3028 1.0000
10.250 1.6117 0.03562 0.02808 -0.0615 0.3009 1.0000
10.500 1.6122 0.03656 0.02916 -0.0584 0.2988 1.0000
10.750 1.6150 0.03749 0.03021 -0.0559 0.2967 1.0000
11.000 1.6216 0.03823 0.03103 -0.0538 0.2943 1.0000
11.250 1.6349 0.03873 0.03157 -0.0527 0.2921 1.0000
11.500 1.6643 0.03873 0.03153 -0.0536 0.2895 1.0000
11.750 1.6928 0.03923 0.03200 -0.0545 0.2868 1.0000
12.000 1.6717 0.04090 0.03390 -0.0495 0.2849 1.0000
12.250 1.6554 0.04279 0.03601 -0.0457 0.2827 1.0000
12.500 1.6424 0.04473 0.03811 -0.0426 0.2802 1.0000
12.750 1.6393 0.04626 0.03976 -0.0407 0.2778 1.0000
13.000 1.6514 0.04680 0.04034 -0.0399 0.2752 1.0000
13.250 1.6985 0.04525 0.03866 -0.0419 0.2721 1.0000
13.500 1.7021 0.04663 0.04014 -0.0406 0.2697 1.0000
13.750 1.6581 0.05099 0.04479 -0.0364 0.2673 1.0000
14.000 1.6098 0.05651 0.05059 -0.0332 0.2644 1.0000
14.250 1.5804 0.06111 0.05536 -0.0318 0.2613 1.0000
14.500 1.6076 0.06039 0.05464 -0.0320 0.2586 1.0000
14.750 1.6876 0.05494 0.04897 -0.0340 0.2554 1.0000
15.000 1.6269 0.06252 0.05686 -0.0317 0.2527 1.0000
15.500 1.4071 0.09495 0.08985 -0.0341 0.2402 1.0000
15.750 1.5930 0.07260 0.06727 -0.0315 0.2409 1.0000
16.000 1.1284 0.14845 0.14350 -0.0517 0.1890 1.0000
16.250 1.1525 0.14735 0.14246 -0.0516 0.1877 1.0000
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Polar data table (+)
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