Rhode St. Genese 30 (rhodesg30-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: Rhode St. Genese 30 (rhodesg30-il) Reynolds number: 50,000 Max Cl/Cd: 34.66 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rhodesg30-il-50000.txt Download as CSV file: xf-rhodesg30-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: Rhode St. Genese 30
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3989 0.10672 0.09981 -0.0206 1.0000 0.2136
-10.250 -0.3899 0.10244 0.09557 -0.0201 1.0000 0.2219
-10.000 -0.4050 0.10127 0.09454 -0.0214 1.0000 0.2299
-9.750 -0.3933 0.09684 0.09014 -0.0201 1.0000 0.2431
-9.500 -0.3908 0.09344 0.08681 -0.0192 1.0000 0.2570
-9.250 -0.3940 0.09067 0.08412 -0.0181 1.0000 0.2734
-9.000 -0.4020 0.08833 0.08190 -0.0166 1.0000 0.2902
-8.750 -0.3900 0.08443 0.07803 -0.0127 1.0000 0.3333
-8.500 -0.4311 0.08455 0.07846 -0.0131 1.0000 0.3233
-8.250 -0.3761 0.07929 0.07289 -0.0054 1.0000 0.4111
-8.000 -0.3723 0.07734 0.07096 -0.0019 1.0000 0.4436
-7.750 -0.3575 0.07529 0.06888 0.0022 1.0000 0.4909
-7.500 -0.3611 0.07403 0.06770 0.0066 1.0000 0.5234
-7.250 -0.3136 0.06992 0.06339 0.0066 1.0000 0.5616
-7.000 -0.3190 0.06907 0.06263 0.0117 1.0000 0.6004
-6.750 -0.2730 0.06517 0.05859 0.0108 1.0000 0.6391
-6.500 -0.2559 0.06342 0.05684 0.0141 1.0000 0.6935
-5.500 -0.3865 0.04604 0.03884 -0.0216 1.0000 0.2755
-5.250 -0.3609 0.04245 0.03468 -0.0244 1.0000 0.2432
-5.000 -0.3384 0.03988 0.03168 -0.0254 1.0000 0.2265
-4.750 -0.3151 0.03779 0.02902 -0.0260 1.0000 0.2135
-4.500 -0.2950 0.03615 0.02719 -0.0256 1.0000 0.2085
-4.250 -0.2716 0.03469 0.02515 -0.0258 1.0000 0.2015
-4.000 -0.2500 0.03362 0.02377 -0.0253 1.0000 0.1988
-3.750 -0.2291 0.03254 0.02250 -0.0248 1.0000 0.1974
-3.500 -0.2079 0.03159 0.02135 -0.0243 1.0000 0.1953
-3.250 -0.1866 0.03075 0.02030 -0.0238 1.0000 0.1933
-3.000 -0.1653 0.03004 0.01936 -0.0232 1.0000 0.1914
-2.750 -0.1441 0.02945 0.01853 -0.0226 1.0000 0.1895
-2.500 -0.1230 0.02898 0.01787 -0.0221 1.0000 0.1885
-2.250 -0.1020 0.02862 0.01737 -0.0216 1.0000 0.1881
-2.000 -0.0826 0.02837 0.01703 -0.0209 1.0000 0.1885
-1.750 -0.0499 0.02832 0.01692 -0.0226 0.9948 0.1901
-1.500 0.0126 0.02849 0.01699 -0.0294 0.9764 0.1951
-1.250 0.0750 0.02851 0.01701 -0.0360 0.9574 0.2048
-1.000 0.1293 0.02835 0.01699 -0.0411 0.9365 0.2227
-0.750 0.2048 0.02536 0.01671 -0.0492 0.9184 1.0000
-0.500 0.2712 0.02575 0.01650 -0.0554 0.8953 1.0000
-0.250 0.3267 0.02588 0.01642 -0.0599 0.8688 1.0000
0.000 0.3835 0.02577 0.01618 -0.0642 0.8418 1.0000
0.250 0.4372 0.02549 0.01583 -0.0676 0.8160 1.0000
0.500 0.4876 0.02507 0.01533 -0.0700 0.7921 1.0000
0.750 0.5224 0.02496 0.01516 -0.0700 0.7656 1.0000
1.000 0.5604 0.02474 0.01488 -0.0704 0.7442 1.0000
1.250 0.5878 0.02496 0.01504 -0.0696 0.7219 1.0000
1.500 0.6181 0.02517 0.01519 -0.0693 0.7045 1.0000
1.750 0.6459 0.02554 0.01554 -0.0688 0.6885 1.0000
2.000 0.6712 0.02607 0.01606 -0.0682 0.6737 1.0000
2.250 0.6943 0.02679 0.01678 -0.0674 0.6601 1.0000
2.500 0.7159 0.02770 0.01771 -0.0667 0.6481 1.0000
2.750 0.7413 0.02846 0.01853 -0.0664 0.6387 1.0000
3.000 0.7624 0.02949 0.01963 -0.0657 0.6287 1.0000
3.250 0.7781 0.03092 0.02116 -0.0648 0.6188 1.0000
3.500 0.8067 0.03157 0.02187 -0.0647 0.6116 1.0000
3.750 0.8125 0.03384 0.02431 -0.0634 0.6025 1.0000
4.000 0.8443 0.03431 0.02487 -0.0634 0.5960 1.0000
4.250 0.8443 0.03696 0.02767 -0.0617 0.5859 1.0000
4.500 0.8624 0.03807 0.02890 -0.0605 0.5747 1.0000
4.750 0.8893 0.03826 0.02923 -0.0593 0.5615 1.0000
5.000 0.9182 0.03830 0.02939 -0.0582 0.5482 1.0000
5.250 0.9433 0.03840 0.02964 -0.0566 0.5327 1.0000
5.500 0.9922 0.03546 0.02668 -0.0548 0.5059 1.0000
5.750 1.0094 0.03564 0.02702 -0.0524 0.4848 1.0000
6.000 1.0439 0.03422 0.02559 -0.0506 0.4594 1.0000
6.250 1.0657 0.03400 0.02550 -0.0484 0.4359 1.0000
6.500 1.0885 0.03330 0.02483 -0.0459 0.4058 1.0000
6.750 1.1058 0.03255 0.02405 -0.0425 0.3676 1.0000
7.000 1.1078 0.03196 0.02340 -0.0371 0.3133 1.0000
7.250 1.0968 0.03240 0.02369 -0.0308 0.2481 1.0000
7.500 1.0927 0.03371 0.02451 -0.0262 0.2010 1.0000
7.750 1.0983 0.03566 0.02604 -0.0232 0.1760 1.0000
8.000 1.1117 0.03791 0.02794 -0.0215 0.1573 1.0000
8.250 1.1389 0.04059 0.03044 -0.0212 0.1426 1.0000
8.500 1.1597 0.04327 0.03336 -0.0203 0.1327 1.0000
8.750 1.1818 0.04632 0.03654 -0.0198 0.1241 1.0000
9.000 1.1996 0.04942 0.03991 -0.0187 0.1185 1.0000
9.250 1.2177 0.05311 0.04369 -0.0181 0.1129 1.0000
9.500 1.2137 0.05621 0.04730 -0.0152 0.1103 1.0000
9.750 1.2096 0.05973 0.05122 -0.0127 0.1086 1.0000
10.000 1.1997 0.06338 0.05522 -0.0100 0.1080 1.0000
10.250 1.1826 0.06711 0.05925 -0.0072 0.1077 1.0000
10.500 1.1598 0.07126 0.06367 -0.0053 0.1081 1.0000
10.750 1.1326 0.07613 0.06878 -0.0046 0.1091 1.0000
11.000 1.1022 0.08193 0.07478 -0.0054 0.1102 1.0000
11.250 1.0715 0.08882 0.08182 -0.0077 0.1116 1.0000
11.500 1.0431 0.09662 0.08970 -0.0112 0.1129 1.0000
11.750 1.0219 0.10470 0.09783 -0.0147 0.1140 1.0000
12.000 0.8784 0.14281 0.13560 -0.0421 0.1444 1.0000
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Polar data table (+)
Polar graphs
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