Rhode St. Genese 34 (rhodesg34-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Rhode St. Genese 34 (rhodesg34-il) Reynolds number: 50,000 Max Cl/Cd: 30.9 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rhodesg34-il-50000-n5.txt Download as CSV file: xf-rhodesg34-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2589 0.12798 0.12083 -0.0381 1.0000 0.1419
-12.250 -0.2768 0.12754 0.12052 -0.0376 1.0000 0.1428
-11.750 -0.3002 0.12483 0.11803 -0.0345 1.0000 0.1436
-11.500 -0.2944 0.12177 0.11502 -0.0321 1.0000 0.1445
-11.250 -0.2948 0.11959 0.11289 -0.0300 1.0000 0.1454
-11.000 -0.2974 0.11771 0.11108 -0.0279 1.0000 0.1467
-10.750 -0.3019 0.11603 0.10947 -0.0260 1.0000 0.1486
-10.500 -0.3003 0.11358 0.10706 -0.0266 0.9976 0.1504
-9.500 -0.2944 0.09281 0.08617 -0.0484 0.9674 0.0942
-9.000 -0.3045 0.08130 0.07453 -0.0601 0.9469 0.0858
-8.750 -0.2890 0.07753 0.07071 -0.0632 0.9407 0.0848
-8.500 -0.2857 0.07386 0.06698 -0.0648 0.9316 0.0839
-8.250 -0.2747 0.06932 0.06228 -0.0685 0.9247 0.0835
-8.000 -0.2716 0.06555 0.05835 -0.0697 0.9159 0.0835
-7.750 -0.2589 0.06130 0.05383 -0.0723 0.9088 0.0838
-7.500 -0.2481 0.05769 0.04994 -0.0733 0.9007 0.0839
-7.250 -0.2321 0.05419 0.04612 -0.0745 0.8927 0.0836
-7.000 -0.2091 0.05055 0.04207 -0.0763 0.8859 0.0835
-6.750 -0.1931 0.04775 0.03889 -0.0760 0.8759 0.0836
-6.500 -0.1583 0.04422 0.03473 -0.0786 0.8693 0.0850
-6.250 -0.1395 0.04202 0.03209 -0.0776 0.8573 0.0866
-6.000 -0.1028 0.04037 0.03034 -0.0792 0.8479 0.0889
-5.750 -0.0687 0.03844 0.02809 -0.0801 0.8372 0.0907
-5.500 -0.0385 0.03669 0.02601 -0.0801 0.8260 0.0925
-5.250 0.0003 0.03482 0.02368 -0.0813 0.8176 0.0960
-5.000 0.0234 0.03408 0.02297 -0.0803 0.8060 0.0991
-4.750 0.0610 0.03288 0.02159 -0.0813 0.7991 0.1034
-4.500 0.0823 0.03211 0.02065 -0.0797 0.7876 0.1068
-4.250 0.1203 0.03121 0.01975 -0.0808 0.7806 0.1131
-4.000 0.1401 0.03074 0.01918 -0.0790 0.7679 0.1189
-3.750 0.1690 0.03011 0.01851 -0.0786 0.7574 0.1264
-3.500 0.2019 0.02936 0.01771 -0.0788 0.7472 0.1375
-3.250 0.2229 0.02888 0.01721 -0.0771 0.7334 0.1490
-3.000 0.2459 0.02827 0.01661 -0.0758 0.7200 0.1669
-2.750 0.2709 0.02746 0.01592 -0.0747 0.7070 0.1957
-2.250 0.3207 0.02556 0.01472 -0.0728 0.6799 0.3313
-2.000 0.4225 0.02315 0.01410 -0.0842 0.6626 1.0000
-1.750 0.4466 0.02296 0.01358 -0.0829 0.6449 1.0000
-1.500 0.4721 0.02279 0.01308 -0.0817 0.6266 1.0000
-1.250 0.4976 0.02270 0.01266 -0.0807 0.6076 1.0000
-1.000 0.5208 0.02274 0.01240 -0.0794 0.5876 1.0000
-0.750 0.5429 0.02289 0.01228 -0.0780 0.5683 1.0000
-0.500 0.5649 0.02309 0.01222 -0.0767 0.5503 1.0000
-0.250 0.5871 0.02334 0.01221 -0.0755 0.5343 1.0000
0.000 0.6078 0.02367 0.01233 -0.0742 0.5193 1.0000
0.250 0.6294 0.02402 0.01247 -0.0731 0.5066 1.0000
0.500 0.6529 0.02434 0.01254 -0.0722 0.4965 1.0000
0.750 0.6747 0.02475 0.01279 -0.0712 0.4866 1.0000
1.000 0.6989 0.02513 0.01297 -0.0706 0.4788 1.0000
1.250 0.7213 0.02560 0.01332 -0.0698 0.4712 1.0000
1.500 0.7476 0.02600 0.01354 -0.0696 0.4656 1.0000
1.750 0.7709 0.02652 0.01399 -0.0690 0.4600 1.0000
2.000 0.7944 0.02706 0.01447 -0.0685 0.4548 1.0000
2.250 0.8206 0.02755 0.01486 -0.0684 0.4503 1.0000
2.500 0.8490 0.02802 0.01520 -0.0686 0.4465 1.0000
2.750 0.8687 0.02873 0.01594 -0.0677 0.4418 1.0000
3.000 0.8909 0.02939 0.01661 -0.0671 0.4376 1.0000
3.250 0.9155 0.02999 0.01717 -0.0668 0.4339 1.0000
3.500 0.9433 0.03055 0.01766 -0.0670 0.4308 1.0000
3.750 0.9666 0.03128 0.01840 -0.0667 0.4278 1.0000
4.000 0.9834 0.03222 0.01945 -0.0656 0.4247 1.0000
4.250 1.0015 0.03316 0.02047 -0.0646 0.4219 1.0000
4.500 1.0206 0.03409 0.02148 -0.0638 0.4192 1.0000
4.750 1.0412 0.03501 0.02244 -0.0632 0.4168 1.0000
5.000 1.0639 0.03586 0.02332 -0.0629 0.4144 1.0000
5.250 1.0901 0.03664 0.02412 -0.0631 0.4122 1.0000
5.500 1.1015 0.03793 0.02553 -0.0614 0.4095 1.0000
5.750 1.1022 0.03963 0.02742 -0.0586 0.4065 1.0000
6.000 1.1038 0.04140 0.02934 -0.0560 0.4038 1.0000
6.250 1.1059 0.04320 0.03127 -0.0535 0.4012 1.0000
6.500 1.1111 0.04484 0.03301 -0.0514 0.3985 1.0000
6.750 1.1318 0.04582 0.03406 -0.0510 0.3957 1.0000
7.000 1.1592 0.04651 0.03476 -0.0513 0.3923 1.0000
7.250 0.9337 0.06626 0.05491 -0.0387 0.3822 1.0000
7.500 0.9534 0.06707 0.05576 -0.0381 0.3785 1.0000
7.750 1.0200 0.06270 0.05140 -0.0376 0.3765 1.0000
8.250 0.9510 0.07596 0.06480 -0.0366 0.3580 1.0000
8.500 1.0104 0.07145 0.06032 -0.0350 0.3562 1.0000
9.000 0.9564 0.08439 0.07343 -0.0359 0.3379 1.0000
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Polar data table (+)
Polar graphs
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