Rhode St. Genese 34 (rhodesg34-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Rhode St. Genese 34 (rhodesg34-il) Reynolds number: 100,000 Max Cl/Cd: 45.6 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rhodesg34-il-100000-n5.txt Download as CSV file: xf-rhodesg34-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Rhode St. Genese 34
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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.2538 0.12533 0.12007 -0.0422 1.0000 0.0761
-13.000 -0.2663 0.12355 0.11839 -0.0425 1.0000 0.0767
-12.750 -0.2828 0.12228 0.11721 -0.0414 1.0000 0.0769
-12.250 -0.2537 0.11434 0.10929 -0.0459 0.9906 0.0780
-12.000 -0.2345 0.11093 0.10587 -0.0477 0.9854 0.0791
-11.750 -0.2182 0.10760 0.10254 -0.0505 0.9799 0.0810
-11.500 -0.2101 0.10401 0.09895 -0.0550 0.9725 0.0847
-11.250 -0.2204 0.09923 0.09418 -0.0643 0.9627 0.0862
-10.750 -0.1965 0.08605 0.08090 -0.0719 0.9515 0.0617
-10.500 -0.1797 0.08249 0.07732 -0.0747 0.9447 0.0596
-10.250 -0.1656 0.07771 0.07251 -0.0802 0.9389 0.0583
-10.000 -0.1641 0.07273 0.06752 -0.0853 0.9285 0.0572
-9.750 -0.1692 0.06647 0.06120 -0.0925 0.9178 0.0564
-9.500 -0.1699 0.06011 0.05470 -0.0988 0.9083 0.0564
-9.250 -0.1776 0.05381 0.04815 -0.1023 0.8977 0.0560
-9.000 -0.1890 0.04544 0.03915 -0.1054 0.8891 0.0551
-8.750 -0.1899 0.04137 0.03462 -0.1043 0.8788 0.0549
-8.500 -0.1725 0.03837 0.03125 -0.1046 0.8719 0.0551
-8.250 -0.1588 0.03623 0.02882 -0.1034 0.8636 0.0555
-8.000 -0.1400 0.03421 0.02650 -0.1027 0.8562 0.0560
-7.750 -0.1161 0.03246 0.02446 -0.1027 0.8502 0.0570
-7.500 -0.1002 0.03109 0.02282 -0.1009 0.8410 0.0582
-7.250 -0.0748 0.02937 0.02069 -0.1007 0.8348 0.0596
-7.000 -0.0566 0.02810 0.01906 -0.0990 0.8259 0.0604
-6.750 -0.0315 0.02682 0.01744 -0.0983 0.8188 0.0612
-6.500 -0.0068 0.02578 0.01633 -0.0976 0.8115 0.0621
-6.250 0.0164 0.02493 0.01539 -0.0966 0.8027 0.0632
-6.000 0.0439 0.02408 0.01441 -0.0962 0.7956 0.0650
-5.750 0.0653 0.02344 0.01364 -0.0947 0.7856 0.0671
-5.500 0.0921 0.02267 0.01270 -0.0941 0.7776 0.0692
-5.250 0.1138 0.02199 0.01205 -0.0927 0.7667 0.0709
-5.000 0.1370 0.02138 0.01142 -0.0915 0.7567 0.0729
-4.750 0.1617 0.02079 0.01076 -0.0906 0.7474 0.0753
-4.500 0.1823 0.02029 0.01027 -0.0890 0.7359 0.0784
-4.250 0.2053 0.01977 0.00979 -0.0878 0.7251 0.0823
-3.750 0.2492 0.01889 0.00893 -0.0850 0.6994 0.0910
-3.500 0.2720 0.01851 0.00857 -0.0837 0.6855 0.0979
-3.250 0.2963 0.01815 0.00825 -0.0826 0.6709 0.1073
-3.000 0.3215 0.01784 0.00798 -0.0817 0.6549 0.1248
-2.750 0.3469 0.01756 0.00764 -0.0808 0.6373 0.1546
-2.500 0.3714 0.01725 0.00733 -0.0798 0.6176 0.1876
-2.250 0.3950 0.01701 0.00710 -0.0788 0.5955 0.2253
-2.000 0.4178 0.01676 0.00696 -0.0777 0.5705 0.2876
-1.750 0.4378 0.01628 0.00693 -0.0763 0.5415 0.4369
-1.250 0.5680 0.01588 0.00713 -0.0899 0.4638 1.0000
-1.000 0.5848 0.01618 0.00716 -0.0878 0.4482 1.0000
-0.750 0.6030 0.01646 0.00723 -0.0861 0.4366 1.0000
-0.500 0.6218 0.01677 0.00732 -0.0844 0.4274 1.0000
-0.250 0.6418 0.01704 0.00744 -0.0829 0.4197 1.0000
0.000 0.6620 0.01736 0.00756 -0.0815 0.4133 1.0000
0.250 0.6833 0.01765 0.00771 -0.0803 0.4080 1.0000
0.500 0.7050 0.01793 0.00789 -0.0792 0.4030 1.0000
0.750 0.7270 0.01824 0.00807 -0.0782 0.3985 1.0000
1.000 0.7498 0.01858 0.00826 -0.0773 0.3946 1.0000
1.250 0.7730 0.01890 0.00848 -0.0766 0.3909 1.0000
1.500 0.7960 0.01920 0.00874 -0.0758 0.3871 1.0000
1.750 0.8193 0.01953 0.00900 -0.0751 0.3837 1.0000
2.000 0.8432 0.01987 0.00927 -0.0745 0.3807 1.0000
2.250 0.8676 0.02024 0.00956 -0.0740 0.3781 1.0000
2.500 0.8932 0.02063 0.00986 -0.0738 0.3758 1.0000
2.750 0.9188 0.02104 0.01020 -0.0735 0.3736 1.0000
3.000 0.9420 0.02140 0.01059 -0.0729 0.3712 1.0000
3.250 0.9655 0.02178 0.01099 -0.0723 0.3686 1.0000
3.500 0.9890 0.02218 0.01140 -0.0718 0.3660 1.0000
3.750 1.0125 0.02259 0.01180 -0.0713 0.3632 1.0000
4.000 1.0364 0.02301 0.01219 -0.0709 0.3604 1.0000
4.250 1.0612 0.02345 0.01260 -0.0706 0.3578 1.0000
4.500 1.0875 0.02395 0.01303 -0.0707 0.3553 1.0000
4.750 1.1078 0.02439 0.01357 -0.0697 0.3528 1.0000
5.000 1.1286 0.02485 0.01413 -0.0688 0.3502 1.0000
5.250 1.1496 0.02531 0.01466 -0.0680 0.3475 1.0000
5.500 1.1708 0.02578 0.01517 -0.0673 0.3444 1.0000
5.750 1.1926 0.02622 0.01563 -0.0666 0.3412 1.0000
6.000 1.2165 0.02668 0.01605 -0.0663 0.3379 1.0000
6.250 1.2365 0.02719 0.01661 -0.0654 0.3348 1.0000
6.500 1.2500 0.02767 0.01726 -0.0635 0.3309 1.0000
6.750 1.2649 0.02812 0.01780 -0.0617 0.3266 1.0000
7.000 1.2828 0.02854 0.01825 -0.0605 0.3225 1.0000
7.250 1.3041 0.02897 0.01868 -0.0599 0.3193 1.0000
7.500 1.3238 0.02951 0.01927 -0.0591 0.3165 1.0000
7.750 1.3332 0.03012 0.02007 -0.0566 0.3134 1.0000
8.000 1.3415 0.03068 0.02078 -0.0540 0.3097 1.0000
8.250 1.3523 0.03119 0.02137 -0.0518 0.3058 1.0000
8.500 1.3671 0.03162 0.02184 -0.0502 0.3020 1.0000
8.750 1.3839 0.03207 0.02229 -0.0491 0.2985 1.0000
9.000 1.3821 0.03293 0.02339 -0.0454 0.2944 1.0000
9.250 1.3858 0.03374 0.02435 -0.0428 0.2899 1.0000
9.500 1.3947 0.03442 0.02513 -0.0409 0.2861 1.0000
9.750 1.4078 0.03499 0.02575 -0.0395 0.2827 1.0000
10.000 1.4105 0.03607 0.02700 -0.0373 0.2790 1.0000
10.250 1.4088 0.03745 0.02860 -0.0348 0.2746 1.0000
10.500 1.4111 0.03865 0.02995 -0.0329 0.2702 1.0000
10.750 1.4183 0.03953 0.03089 -0.0314 0.2658 1.0000
11.000 1.4118 0.04155 0.03315 -0.0293 0.2610 1.0000
11.250 1.4053 0.04369 0.03549 -0.0275 0.2556 1.0000
11.500 1.4063 0.04527 0.03717 -0.0262 0.2506 1.0000
11.750 1.3901 0.04865 0.04081 -0.0247 0.2445 1.0000
12.000 1.3755 0.05208 0.04442 -0.0236 0.2379 1.0000
12.250 1.3464 0.05752 0.05009 -0.0231 0.2312 1.0000
12.500 1.2884 0.06740 0.06020 -0.0242 0.2238 1.0000
12.750 1.1788 0.08701 0.08001 -0.0294 0.2090 1.0000
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Polar data table (+)
Polar graphs
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