Rhode St. Genese 30 (rhodesg30-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Rhode St. Genese 30 (rhodesg30-il) Reynolds number: 200,000 Max Cl/Cd: 67.11 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rhodesg30-il-200000.txt Download as CSV file: xf-rhodesg30-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4304 0.09027 0.08671 -0.0323 1.0000 0.0311
-10.750 -0.4772 0.07720 0.07378 -0.0395 1.0000 0.0283
-10.500 -0.7031 0.03260 0.02823 -0.0572 1.0000 0.0226
-10.250 -0.7051 0.02898 0.02414 -0.0545 1.0000 0.0229
-10.000 -0.6990 0.02663 0.02142 -0.0519 1.0000 0.0232
-9.750 -0.6893 0.02472 0.01918 -0.0496 1.0000 0.0236
-9.500 -0.6758 0.02342 0.01764 -0.0475 1.0000 0.0239
-9.250 -0.6597 0.02265 0.01674 -0.0456 1.0000 0.0244
-9.000 -0.6423 0.02207 0.01606 -0.0438 1.0000 0.0248
-8.750 -0.6236 0.02189 0.01586 -0.0421 1.0000 0.0254
-8.500 -0.6037 0.02226 0.01632 -0.0406 1.0000 0.0261
-8.250 -0.5828 0.02334 0.01762 -0.0392 1.0000 0.0272
-8.000 -0.5623 0.02445 0.01890 -0.0378 1.0000 0.0283
-7.750 -0.5380 0.02292 0.01701 -0.0375 0.9986 0.0334
-7.500 -0.5032 0.02079 0.01416 -0.0390 0.9951 0.0395
-7.250 -0.4643 0.02103 0.01430 -0.0412 0.9902 0.0424
-7.000 -0.4221 0.02125 0.01436 -0.0440 0.9850 0.0458
-6.750 -0.3811 0.02166 0.01450 -0.0464 0.9787 0.0486
-6.500 -0.3402 0.02124 0.01416 -0.0494 0.9731 0.0510
-6.250 -0.3001 0.02146 0.01443 -0.0520 0.9677 0.0541
-6.000 -0.2615 0.02193 0.01478 -0.0540 0.9609 0.0580
-5.750 -0.2204 0.02095 0.01370 -0.0571 0.9571 0.0615
-5.500 -0.1856 0.02109 0.01394 -0.0588 0.9496 0.0675
-5.250 -0.1429 0.02154 0.01420 -0.0614 0.9447 0.0708
-5.000 -0.1018 0.01978 0.01248 -0.0648 0.9420 0.0768
-4.750 -0.0689 0.01951 0.01213 -0.0657 0.9339 0.0812
-4.500 -0.0282 0.01907 0.01152 -0.0679 0.9288 0.0833
-4.250 0.0044 0.01788 0.01033 -0.0691 0.9212 0.0890
-4.000 0.0406 0.01699 0.00930 -0.0702 0.9137 0.0886
-3.750 0.0714 0.01625 0.00843 -0.0702 0.9041 0.0869
-3.500 0.1049 0.01566 0.00773 -0.0708 0.8969 0.0858
-3.250 0.1314 0.01521 0.00724 -0.0700 0.8861 0.0853
-3.000 0.1595 0.01472 0.00672 -0.0696 0.8763 0.0850
-2.750 0.1879 0.01420 0.00618 -0.0693 0.8667 0.0850
-2.500 0.2126 0.01373 0.00571 -0.0682 0.8542 0.0854
-2.250 0.2378 0.01329 0.00529 -0.0673 0.8417 0.0859
-2.000 0.2630 0.01291 0.00491 -0.0664 0.8288 0.0867
-1.750 0.2883 0.01257 0.00458 -0.0655 0.8153 0.0877
-1.500 0.3137 0.01230 0.00430 -0.0646 0.8010 0.0895
-1.250 0.3391 0.01207 0.00406 -0.0637 0.7851 0.0928
-1.000 0.3646 0.01189 0.00383 -0.0629 0.7676 0.0958
-0.750 0.3904 0.01174 0.00362 -0.0620 0.7485 0.0984
-0.500 0.4155 0.01160 0.00345 -0.0610 0.7259 0.1036
-0.250 0.4402 0.01148 0.00334 -0.0600 0.6999 0.1206
0.000 0.4490 0.00961 0.00341 -0.0563 0.6724 0.7323
0.250 0.5352 0.00949 0.00336 -0.0677 0.6076 1.0000
0.500 0.5549 0.00981 0.00338 -0.0658 0.5578 1.0000
0.750 0.5748 0.01018 0.00344 -0.0642 0.5166 1.0000
1.000 0.5959 0.01054 0.00355 -0.0628 0.4892 1.0000
1.250 0.6180 0.01088 0.00371 -0.0617 0.4703 1.0000
1.500 0.6408 0.01120 0.00390 -0.0607 0.4562 1.0000
1.750 0.6640 0.01154 0.00410 -0.0598 0.4450 1.0000
2.000 0.6880 0.01182 0.00432 -0.0591 0.4356 1.0000
2.250 0.7123 0.01215 0.00456 -0.0584 0.4283 1.0000
2.500 0.7362 0.01244 0.00481 -0.0577 0.4191 1.0000
2.750 0.7600 0.01271 0.00506 -0.0570 0.4086 1.0000
3.000 0.7837 0.01304 0.00531 -0.0562 0.3991 1.0000
3.250 0.8076 0.01328 0.00558 -0.0555 0.3900 1.0000
3.500 0.8316 0.01357 0.00586 -0.0549 0.3816 1.0000
3.750 0.8558 0.01384 0.00614 -0.0543 0.3741 1.0000
4.000 0.8800 0.01413 0.00646 -0.0537 0.3669 1.0000
4.250 0.9036 0.01438 0.00673 -0.0530 0.3578 1.0000
4.500 0.9265 0.01458 0.00700 -0.0521 0.3469 1.0000
4.750 0.9489 0.01479 0.00724 -0.0512 0.3345 1.0000
5.000 0.9712 0.01500 0.00750 -0.0503 0.3225 1.0000
5.250 0.9931 0.01518 0.00774 -0.0493 0.3087 1.0000
5.500 1.0148 0.01528 0.00795 -0.0482 0.2886 1.0000
5.750 1.0355 0.01543 0.00813 -0.0469 0.2529 1.0000
6.000 1.0426 0.01690 0.00885 -0.0441 0.1327 1.0000
6.250 1.0548 0.01823 0.00992 -0.0419 0.0880 1.0000
6.500 1.0703 0.01916 0.01076 -0.0401 0.0730 1.0000
6.750 1.0844 0.02011 0.01169 -0.0382 0.0664 1.0000
7.000 1.0975 0.02107 0.01273 -0.0360 0.0626 1.0000
7.250 1.1097 0.02204 0.01380 -0.0338 0.0593 1.0000
7.500 1.1178 0.02324 0.01503 -0.0311 0.0561 1.0000
7.750 1.1197 0.02479 0.01658 -0.0274 0.0536 1.0000
8.000 1.1297 0.02585 0.01775 -0.0250 0.0518 1.0000
8.250 1.1396 0.02702 0.01902 -0.0227 0.0494 1.0000
8.500 1.1489 0.02837 0.02043 -0.0205 0.0469 1.0000
8.750 1.1596 0.03005 0.02210 -0.0187 0.0446 1.0000
9.000 1.1794 0.03269 0.02477 -0.0182 0.0416 1.0000
9.250 1.1906 0.03386 0.02612 -0.0163 0.0398 1.0000
9.500 1.2058 0.03556 0.02796 -0.0151 0.0379 1.0000
9.750 1.2204 0.03734 0.02984 -0.0139 0.0360 1.0000
10.000 1.2367 0.03948 0.03204 -0.0133 0.0342 1.0000
10.250 1.2555 0.04390 0.03667 -0.0135 0.0320 1.0000
10.500 1.2538 0.04540 0.03842 -0.0105 0.0314 1.0000
10.750 1.2537 0.04763 0.04091 -0.0082 0.0309 1.0000
11.000 1.2507 0.05012 0.04366 -0.0060 0.0303 1.0000
11.250 1.2454 0.05297 0.04677 -0.0041 0.0299 1.0000
11.500 1.2374 0.05604 0.05008 -0.0026 0.0296 1.0000
11.750 1.2268 0.05938 0.05367 -0.0014 0.0292 1.0000
12.000 1.2145 0.06302 0.05753 -0.0008 0.0288 1.0000
12.250 1.2001 0.06717 0.06191 -0.0008 0.0288 1.0000
12.500 1.1883 0.07096 0.06586 -0.0014 0.0279 1.0000
12.750 1.1679 0.07644 0.07158 -0.0029 0.0281 1.0000
13.000 1.1438 0.08300 0.07840 -0.0053 0.0288 1.0000
13.250 1.1243 0.08904 0.08462 -0.0083 0.0286 1.0000
13.500 1.0965 0.09727 0.09307 -0.0128 0.0293 1.0000
13.750 1.0701 0.10605 0.10203 -0.0179 0.0300 1.0000
14.000 1.0425 0.11581 0.11194 -0.0237 0.0308 1.0000
14.250 1.0167 0.12590 0.12215 -0.0297 0.0314 1.0000
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Polar data table (+)
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