Rhode St. Genese 30 (rhodesg30-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Rhode St. Genese 30 (rhodesg30-il) Reynolds number: 50,000 Max Cl/Cd: 36.27 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rhodesg30-il-50000-n5.txt Download as CSV file: xf-rhodesg30-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4033 0.09576 0.08880 -0.0346 1.0000 0.0405
-10.500 -0.4043 0.09215 0.08527 -0.0357 1.0000 0.0408
-10.250 -0.4073 0.08843 0.08165 -0.0369 1.0000 0.0412
-10.000 -0.4129 0.08466 0.07799 -0.0381 1.0000 0.0414
-9.750 -0.4218 0.08097 0.07443 -0.0391 1.0000 0.0416
-9.500 -0.4316 0.07704 0.07063 -0.0404 1.0000 0.0419
-9.250 -0.4401 0.07274 0.06641 -0.0421 1.0000 0.0421
-9.000 -0.4485 0.06824 0.06197 -0.0434 1.0000 0.0424
-8.750 -0.4565 0.06362 0.05734 -0.0443 1.0000 0.0431
-8.500 -0.4647 0.05849 0.05212 -0.0449 1.0000 0.0441
-8.250 -0.4743 0.05204 0.04538 -0.0456 1.0000 0.0457
-8.000 -0.4737 0.04788 0.04093 -0.0451 1.0000 0.0487
-7.750 -0.4670 0.04505 0.03778 -0.0441 1.0000 0.0538
-7.500 -0.4595 0.04133 0.03349 -0.0434 1.0000 0.0591
-7.250 -0.4457 0.04112 0.03327 -0.0419 1.0000 0.0660
-7.000 -0.4323 0.03836 0.02989 -0.0409 1.0000 0.0696
-6.750 -0.4162 0.03629 0.02722 -0.0399 1.0000 0.0712
-6.500 -0.3999 0.03525 0.02609 -0.0387 1.0000 0.0733
-6.250 -0.3837 0.03523 0.02611 -0.0374 1.0000 0.0792
-6.000 -0.3657 0.03423 0.02467 -0.0364 1.0000 0.0833
-5.750 -0.3469 0.03321 0.02322 -0.0355 1.0000 0.0848
-5.500 -0.3269 0.03248 0.02242 -0.0349 0.9992 0.0866
-5.250 -0.2936 0.03242 0.02233 -0.0369 0.9924 0.0933
-5.000 -0.2588 0.03183 0.02134 -0.0391 0.9858 0.0996
-4.750 -0.2267 0.03144 0.02095 -0.0408 0.9785 0.1043
-4.500 -0.1927 0.03061 0.01983 -0.0424 0.9719 0.1047
-4.250 -0.1570 0.02978 0.01872 -0.0442 0.9648 0.1045
-4.000 -0.1220 0.02902 0.01771 -0.0458 0.9560 0.1047
-3.750 -0.0816 0.02829 0.01677 -0.0483 0.9463 0.1054
-3.500 -0.0365 0.02750 0.01577 -0.0514 0.9349 0.1063
-3.250 0.0081 0.02670 0.01480 -0.0541 0.9209 0.1071
-3.000 0.0532 0.02594 0.01389 -0.0567 0.9067 0.1079
-2.750 0.0947 0.02528 0.01308 -0.0587 0.8936 0.1091
-2.500 0.1322 0.02476 0.01244 -0.0601 0.8822 0.1108
-2.250 0.1694 0.02425 0.01186 -0.0615 0.8721 0.1132
-2.000 0.2029 0.02381 0.01142 -0.0622 0.8606 0.1168
-1.750 0.2335 0.02344 0.01104 -0.0624 0.8474 0.1219
-1.500 0.2638 0.02306 0.01069 -0.0625 0.8338 0.1314
-1.250 0.2937 0.02262 0.01036 -0.0625 0.8198 0.1540
-1.000 0.3536 0.01957 0.01009 -0.0679 0.8085 1.0000
-0.750 0.3813 0.01955 0.00980 -0.0673 0.7919 1.0000
-0.500 0.4090 0.01950 0.00956 -0.0666 0.7744 1.0000
-0.250 0.4370 0.01945 0.00934 -0.0659 0.7564 1.0000
0.000 0.4637 0.01942 0.00915 -0.0651 0.7366 1.0000
0.250 0.4893 0.01943 0.00903 -0.0641 0.7147 1.0000
0.750 0.5427 0.01950 0.00882 -0.0624 0.6687 1.0000
1.000 0.5695 0.01959 0.00876 -0.0617 0.6457 1.0000
1.250 0.5948 0.01979 0.00884 -0.0608 0.6215 1.0000
1.500 0.6204 0.02002 0.00892 -0.0600 0.5993 1.0000
1.750 0.6450 0.02034 0.00915 -0.0592 0.5779 1.0000
2.000 0.6700 0.02069 0.00938 -0.0586 0.5595 1.0000
2.250 0.6951 0.02108 0.00969 -0.0580 0.5436 1.0000
2.500 0.7202 0.02151 0.01009 -0.0575 0.5299 1.0000
2.750 0.7455 0.02197 0.01053 -0.0571 0.5179 1.0000
3.000 0.7713 0.02242 0.01096 -0.0567 0.5075 1.0000
3.250 0.7968 0.02292 0.01150 -0.0564 0.4976 1.0000
3.500 0.8219 0.02346 0.01211 -0.0560 0.4886 1.0000
3.750 0.8484 0.02399 0.01268 -0.0558 0.4815 1.0000
4.000 0.8731 0.02463 0.01347 -0.0556 0.4742 1.0000
4.250 0.8990 0.02522 0.01416 -0.0553 0.4673 1.0000
4.500 0.9229 0.02588 0.01497 -0.0549 0.4595 1.0000
4.750 0.9482 0.02645 0.01564 -0.0544 0.4510 1.0000
5.000 0.9697 0.02709 0.01644 -0.0535 0.4397 1.0000
5.250 0.9904 0.02754 0.01694 -0.0523 0.4241 1.0000
5.500 1.0103 0.02786 0.01724 -0.0507 0.4051 1.0000
5.750 1.0269 0.02831 0.01779 -0.0489 0.3858 1.0000
6.000 1.0446 0.02883 0.01843 -0.0473 0.3696 1.0000
6.250 1.0629 0.02937 0.01913 -0.0459 0.3553 1.0000
6.500 1.0764 0.02990 0.01983 -0.0438 0.3363 1.0000
6.750 1.0883 0.03041 0.02051 -0.0415 0.3161 1.0000
7.000 1.1002 0.03098 0.02128 -0.0392 0.2968 1.0000
7.250 1.1074 0.03167 0.02226 -0.0366 0.2699 1.0000
7.500 1.1139 0.03247 0.02333 -0.0339 0.2346 1.0000
7.750 1.1141 0.03353 0.02417 -0.0306 0.1832 1.0000
8.000 1.1064 0.03544 0.02561 -0.0268 0.1528 1.0000
8.250 1.1011 0.03780 0.02781 -0.0240 0.1329 1.0000
8.500 1.0962 0.04034 0.03029 -0.0216 0.1200 1.0000
8.750 1.0916 0.04299 0.03294 -0.0197 0.1102 1.0000
9.000 1.0899 0.04555 0.03562 -0.0182 0.1015 1.0000
9.250 1.0858 0.04839 0.03848 -0.0171 0.0950 1.0000
9.500 1.0867 0.05100 0.04124 -0.0161 0.0896 1.0000
9.750 1.0873 0.05370 0.04406 -0.0153 0.0852 1.0000
10.000 1.0868 0.05656 0.04693 -0.0148 0.0813 1.0000
10.250 1.0883 0.05940 0.04999 -0.0144 0.0762 1.0000
10.500 1.0881 0.06240 0.05303 -0.0142 0.0722 1.0000
10.750 1.0910 0.06522 0.05593 -0.0138 0.0687 1.0000
11.000 1.0932 0.06831 0.05924 -0.0136 0.0648 1.0000
11.250 1.0948 0.07135 0.06235 -0.0136 0.0611 1.0000
11.500 1.1029 0.07398 0.06501 -0.0127 0.0577 1.0000
11.750 1.1008 0.07807 0.06945 -0.0132 0.0553 1.0000
12.000 1.0966 0.08247 0.07413 -0.0140 0.0531 1.0000
12.250 1.0905 0.08715 0.07902 -0.0153 0.0511 1.0000
12.500 1.0848 0.09196 0.08403 -0.0167 0.0496 1.0000
12.750 1.0784 0.09699 0.08923 -0.0183 0.0484 1.0000
13.000 1.0764 0.10147 0.09378 -0.0193 0.0467 1.0000
13.250 1.0659 0.10761 0.10004 -0.0216 0.0459 1.0000
13.500 1.0481 0.11513 0.10777 -0.0258 0.0459 1.0000
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Polar data table (+)
Polar graphs
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