Rhode St. Genese 30 (rhodesg30-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Rhode St. Genese 30 (rhodesg30-il) Reynolds number: 100,000 Max Cl/Cd: 51.31 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rhodesg30-il-100000.txt Download as CSV file: xf-rhodesg30-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3284 0.09268 0.08807 -0.0333 1.0000 0.0966
-10.500 -0.3958 0.09698 0.09203 -0.0289 1.0000 0.0894
-10.250 -0.3970 0.09395 0.08907 -0.0301 1.0000 0.0938
-10.000 -0.4120 0.09101 0.08624 -0.0337 1.0000 0.0963
-9.750 -0.4359 0.08806 0.08345 -0.0374 1.0000 0.0970
-9.500 -0.4519 0.08412 0.07956 -0.0417 1.0000 0.0973
-9.250 -0.4149 0.08152 0.07697 -0.0319 1.0000 0.1040
-9.000 -0.4818 0.06304 0.05832 -0.0470 1.0000 0.0587
-8.750 -0.4885 0.05867 0.05388 -0.0458 1.0000 0.0585
-8.500 -0.4955 0.05400 0.04906 -0.0446 1.0000 0.0583
-8.250 -0.5041 0.04823 0.04291 -0.0433 1.0000 0.0587
-8.000 -0.4943 0.04764 0.04254 -0.0410 1.0000 0.0616
-7.750 -0.4904 0.04442 0.03912 -0.0394 1.0000 0.0649
-7.500 -0.4923 0.03734 0.03090 -0.0382 1.0000 0.0708
-7.250 -0.4777 0.03708 0.03099 -0.0367 1.0000 0.0761
-7.000 -0.4648 0.03520 0.02858 -0.0352 1.0000 0.0827
-6.750 -0.4496 0.03351 0.02634 -0.0338 1.0000 0.0840
-6.500 -0.4339 0.03372 0.02702 -0.0326 1.0000 0.0907
-6.250 -0.4174 0.03284 0.02579 -0.0313 1.0000 0.0953
-6.000 -0.4019 0.03299 0.02608 -0.0301 1.0000 0.1031
-5.750 -0.3844 0.03202 0.02490 -0.0291 1.0000 0.1046
-5.500 -0.3660 0.03106 0.02370 -0.0281 1.0000 0.1056
-5.250 -0.3472 0.03023 0.02263 -0.0272 1.0000 0.1069
-5.000 -0.3282 0.02980 0.02184 -0.0262 1.0000 0.1102
-4.750 -0.2882 0.02968 0.02188 -0.0299 0.9927 0.1208
-4.500 -0.2381 0.02886 0.02064 -0.0346 0.9832 0.1234
-4.250 -0.1952 0.02818 0.02003 -0.0384 0.9726 0.1332
-4.000 -0.1491 0.02670 0.01792 -0.0415 0.9622 0.1266
-3.750 -0.1019 0.02572 0.01669 -0.0450 0.9527 0.1242
-3.500 -0.0580 0.02454 0.01537 -0.0479 0.9437 0.1224
-3.250 -0.0200 0.02363 0.01433 -0.0497 0.9345 0.1211
-3.000 0.0271 0.02271 0.01330 -0.0531 0.9276 0.1202
-2.750 0.0633 0.02200 0.01253 -0.0544 0.9174 0.1199
-2.500 0.1151 0.02117 0.01168 -0.0584 0.9115 0.1219
-2.250 0.1518 0.02066 0.01114 -0.0597 0.9003 0.1248
-2.000 0.1929 0.01983 0.01047 -0.0618 0.8910 0.1283
-1.750 0.2365 0.01906 0.00980 -0.0640 0.8825 0.1320
-1.500 0.2693 0.01857 0.00933 -0.0642 0.8699 0.1364
-1.250 0.3028 0.01802 0.00884 -0.0645 0.8571 0.1440
-1.000 0.3365 0.01742 0.00834 -0.0647 0.8437 0.1616
-0.750 0.4327 0.01419 0.00754 -0.0765 0.8351 1.0000
-0.500 0.4558 0.01405 0.00726 -0.0747 0.8139 1.0000
-0.250 0.4824 0.01381 0.00688 -0.0733 0.7928 1.0000
0.000 0.5059 0.01364 0.00659 -0.0715 0.7668 1.0000
0.250 0.5302 0.01350 0.00629 -0.0697 0.7370 1.0000
0.500 0.5546 0.01345 0.00603 -0.0681 0.7028 1.0000
0.750 0.5775 0.01358 0.00591 -0.0664 0.6641 1.0000
1.000 0.6007 0.01384 0.00590 -0.0650 0.6294 1.0000
1.250 0.6239 0.01419 0.00601 -0.0637 0.6003 1.0000
1.500 0.6478 0.01456 0.00621 -0.0628 0.5783 1.0000
1.750 0.6719 0.01496 0.00648 -0.0620 0.5604 1.0000
2.000 0.6966 0.01537 0.00679 -0.0614 0.5465 1.0000
2.250 0.7221 0.01579 0.00709 -0.0609 0.5355 1.0000
2.500 0.7467 0.01621 0.00753 -0.0603 0.5245 1.0000
2.750 0.7714 0.01664 0.00795 -0.0598 0.5144 1.0000
3.000 0.7968 0.01706 0.00830 -0.0593 0.5050 1.0000
3.250 0.8210 0.01749 0.00880 -0.0587 0.4953 1.0000
3.500 0.8452 0.01791 0.00924 -0.0580 0.4849 1.0000
3.750 0.8689 0.01829 0.00958 -0.0572 0.4726 1.0000
4.000 0.8915 0.01862 0.00990 -0.0562 0.4577 1.0000
4.250 0.9138 0.01896 0.01021 -0.0552 0.4425 1.0000
4.500 0.9367 0.01933 0.01058 -0.0542 0.4290 1.0000
4.750 0.9603 0.01975 0.01103 -0.0535 0.4177 1.0000
5.000 0.9822 0.02013 0.01154 -0.0525 0.4051 1.0000
5.250 1.0040 0.02050 0.01200 -0.0514 0.3919 1.0000
5.500 1.0249 0.02080 0.01239 -0.0502 0.3769 1.0000
5.750 1.0444 0.02102 0.01267 -0.0487 0.3589 1.0000
6.000 1.0623 0.02118 0.01292 -0.0469 0.3393 1.0000
6.250 1.0767 0.02122 0.01315 -0.0445 0.3131 1.0000
6.500 1.0863 0.02117 0.01329 -0.0412 0.2596 1.0000
6.750 1.0813 0.02308 0.01422 -0.0367 0.1439 1.0000
7.000 1.0842 0.02510 0.01602 -0.0334 0.1173 1.0000
7.250 1.0914 0.02661 0.01754 -0.0305 0.1058 1.0000
7.500 1.0981 0.02810 0.01900 -0.0277 0.0980 1.0000
7.750 1.1071 0.02935 0.02029 -0.0252 0.0910 1.0000
8.000 1.1153 0.03084 0.02175 -0.0227 0.0861 1.0000
8.250 1.1282 0.03218 0.02316 -0.0207 0.0811 1.0000
8.500 1.1442 0.03400 0.02479 -0.0196 0.0758 1.0000
8.750 1.1646 0.03567 0.02667 -0.0186 0.0721 1.0000
9.000 1.1843 0.03750 0.02853 -0.0178 0.0676 1.0000
9.250 1.2176 0.04076 0.03180 -0.0192 0.0635 1.0000
9.500 1.2350 0.04333 0.03471 -0.0180 0.0614 1.0000
9.750 1.2469 0.04581 0.03746 -0.0165 0.0588 1.0000
10.000 1.2574 0.04844 0.04027 -0.0150 0.0566 1.0000
10.250 1.2672 0.05179 0.04387 -0.0137 0.0552 1.0000
10.500 1.2706 0.05541 0.04777 -0.0117 0.0547 1.0000
10.750 1.2664 0.05887 0.05152 -0.0091 0.0545 1.0000
11.000 1.2579 0.06262 0.05554 -0.0067 0.0542 1.0000
11.250 1.2448 0.06644 0.05962 -0.0044 0.0539 1.0000
11.500 1.2280 0.06985 0.06329 -0.0024 0.0540 1.0000
11.750 1.2090 0.07399 0.06767 -0.0014 0.0539 1.0000
12.000 1.1873 0.07786 0.07179 -0.0009 0.0541 1.0000
12.250 0.9943 0.08454 0.07943 -0.0019 0.0596 1.0000
12.500 0.9550 0.09290 0.08800 -0.0060 0.0607 1.0000
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Polar data table (+)
Polar graphs
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