RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG-15 8.9% (rg15-il) Reynolds number: 500,000 Max Cl/Cd: 79.01 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg15-il-500000-n5.txt Download as CSV file: xf-rg15-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG-15 8.9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5275 0.08066 0.07842 -0.0290 1.0000 0.0053
-9.250 -0.5460 0.07314 0.07095 -0.0330 1.0000 0.0052
-9.000 -0.5609 0.06696 0.06484 -0.0370 1.0000 0.0053
-8.750 -0.7166 0.03110 0.02781 -0.0460 1.0000 0.0045
-8.500 -0.7080 0.02861 0.02504 -0.0446 1.0000 0.0047
-8.250 -0.6939 0.02712 0.02338 -0.0433 1.0000 0.0049
-8.000 -0.6743 0.02554 0.02158 -0.0430 0.9994 0.0051
-7.750 -0.6466 0.02332 0.01900 -0.0445 0.9973 0.0055
-7.500 -0.6185 0.02084 0.01612 -0.0459 0.9952 0.0058
-7.250 -0.5903 0.01879 0.01371 -0.0468 0.9931 0.0060
-7.000 -0.5622 0.01709 0.01172 -0.0475 0.9905 0.0063
-6.750 -0.5324 0.01584 0.01025 -0.0483 0.9879 0.0066
-6.500 -0.5012 0.01488 0.00912 -0.0494 0.9856 0.0069
-6.250 -0.4696 0.01375 0.00785 -0.0507 0.9836 0.0077
-6.000 -0.4396 0.01323 0.00727 -0.0514 0.9804 0.0084
-5.750 -0.4099 0.01268 0.00666 -0.0519 0.9765 0.0095
-5.500 -0.3780 0.01218 0.00607 -0.0530 0.9733 0.0106
-5.250 -0.3451 0.01159 0.00543 -0.0543 0.9709 0.0123
-5.000 -0.3158 0.01122 0.00502 -0.0547 0.9663 0.0144
-4.750 -0.2854 0.01084 0.00458 -0.0553 0.9615 0.0161
-4.500 -0.2524 0.01041 0.00408 -0.0565 0.9581 0.0177
-4.250 -0.2222 0.01000 0.00365 -0.0571 0.9526 0.0209
-4.000 -0.1905 0.00968 0.00329 -0.0579 0.9467 0.0235
-3.750 -0.1570 0.00933 0.00293 -0.0592 0.9417 0.0290
-3.500 -0.1257 0.00900 0.00262 -0.0599 0.9340 0.0417
-3.250 -0.0925 0.00867 0.00235 -0.0611 0.9268 0.0647
-3.000 -0.0603 0.00837 0.00213 -0.0621 0.9172 0.0929
-2.750 -0.0293 0.00808 0.00193 -0.0629 0.9056 0.1282
-2.500 0.0004 0.00771 0.00173 -0.0634 0.8923 0.1894
-2.250 0.0286 0.00727 0.00156 -0.0637 0.8773 0.2792
-2.000 0.0559 0.00689 0.00142 -0.0638 0.8610 0.3693
-1.750 0.0829 0.00664 0.00131 -0.0637 0.8436 0.4368
-1.500 0.1085 0.00629 0.00123 -0.0633 0.8254 0.5396
-1.250 0.1341 0.00611 0.00124 -0.0627 0.8065 0.6240
-1.000 0.1605 0.00610 0.00122 -0.0623 0.7873 0.6600
-0.750 0.1869 0.00612 0.00120 -0.0618 0.7673 0.6846
-0.500 0.2132 0.00616 0.00120 -0.0613 0.7471 0.7058
-0.250 0.2395 0.00620 0.00120 -0.0608 0.7260 0.7247
0.000 0.2656 0.00627 0.00121 -0.0603 0.7046 0.7415
0.250 0.2918 0.00634 0.00123 -0.0599 0.6825 0.7568
0.500 0.3178 0.00642 0.00126 -0.0594 0.6604 0.7715
0.750 0.3437 0.00651 0.00129 -0.0588 0.6377 0.7864
1.000 0.3695 0.00660 0.00134 -0.0583 0.6146 0.8014
1.500 0.4202 0.00680 0.00146 -0.0571 0.5671 0.8327
1.750 0.4452 0.00691 0.00153 -0.0564 0.5422 0.8488
2.000 0.4701 0.00704 0.00162 -0.0557 0.5172 0.8636
2.250 0.4948 0.00718 0.00171 -0.0550 0.4909 0.8777
2.500 0.5192 0.00733 0.00180 -0.0542 0.4650 0.8931
2.750 0.5433 0.00748 0.00190 -0.0533 0.4390 0.9106
3.250 0.5961 0.00785 0.00214 -0.0527 0.3823 0.9557
3.500 0.6293 0.00811 0.00228 -0.0540 0.3479 0.9847
3.750 0.6572 0.00837 0.00244 -0.0542 0.3203 1.0000
4.000 0.6825 0.00866 0.00263 -0.0539 0.2926 1.0000
4.250 0.7079 0.00896 0.00285 -0.0535 0.2654 1.0000
4.500 0.7328 0.00932 0.00307 -0.0531 0.2340 1.0000
4.750 0.7573 0.00972 0.00333 -0.0527 0.2010 1.0000
5.000 0.7821 0.01009 0.00360 -0.0523 0.1741 1.0000
5.250 0.8066 0.01051 0.00389 -0.0518 0.1464 1.0000
5.500 0.8312 0.01090 0.00422 -0.0514 0.1240 1.0000
5.750 0.8554 0.01135 0.00457 -0.0509 0.1000 1.0000
6.000 0.8790 0.01186 0.00495 -0.0503 0.0752 1.0000
6.500 0.9267 0.01280 0.00576 -0.0493 0.0445 1.0000
6.750 0.9505 0.01327 0.00618 -0.0487 0.0339 1.0000
7.000 0.9744 0.01372 0.00665 -0.0482 0.0270 1.0000
7.250 0.9977 0.01422 0.00715 -0.0475 0.0191 1.0000
7.500 1.0199 0.01485 0.00774 -0.0468 0.0115 1.0000
7.750 1.0420 0.01550 0.00839 -0.0459 0.0079 1.0000
8.000 1.0648 0.01604 0.00901 -0.0452 0.0070 1.0000
8.250 1.0870 0.01664 0.00969 -0.0444 0.0063 1.0000
8.500 1.1086 0.01728 0.01044 -0.0435 0.0058 1.0000
8.750 1.1291 0.01804 0.01129 -0.0424 0.0052 1.0000
9.000 1.1484 0.01891 0.01228 -0.0412 0.0049 1.0000
9.250 1.1645 0.02010 0.01361 -0.0395 0.0045 1.0000
9.500 1.1811 0.02115 0.01479 -0.0380 0.0044 1.0000
9.750 1.1979 0.02212 0.01588 -0.0365 0.0043 1.0000
10.000 1.2139 0.02311 0.01700 -0.0350 0.0042 1.0000
10.250 1.2297 0.02406 0.01807 -0.0334 0.0040 1.0000
10.500 1.2437 0.02512 0.01928 -0.0317 0.0038 1.0000
10.750 1.2560 0.02620 0.02049 -0.0297 0.0036 1.0000
11.000 1.2638 0.02741 0.02184 -0.0271 0.0035 1.0000
11.250 1.2693 0.02875 0.02332 -0.0243 0.0034 1.0000
11.500 1.2737 0.03017 0.02489 -0.0217 0.0033 1.0000
11.750 1.2761 0.03177 0.02665 -0.0191 0.0032 1.0000
12.000 1.2759 0.03366 0.02871 -0.0166 0.0032 1.0000
12.250 1.2778 0.03543 0.03062 -0.0148 0.0031 1.0000
12.500 1.2761 0.03764 0.03299 -0.0131 0.0030 1.0000
12.750 1.2713 0.04037 0.03589 -0.0118 0.0030 1.0000
13.000 1.2687 0.04303 0.03869 -0.0113 0.0029 1.0000
13.250 1.2611 0.04656 0.04240 -0.0112 0.0029 1.0000
13.500 1.2516 0.05066 0.04669 -0.0119 0.0029 1.0000
13.750 1.2432 0.05500 0.05119 -0.0134 0.0028 1.0000
14.000 1.2292 0.06059 0.05698 -0.0158 0.0028 1.0000
14.250 1.2194 0.06598 0.06250 -0.0186 0.0028 1.0000
14.500 1.1990 0.07365 0.07040 -0.0227 0.0029 1.0000
14.750 1.1858 0.08051 0.07739 -0.0268 0.0028 1.0000
15.000 1.1652 0.08920 0.08627 -0.0320 0.0029 1.0000
15.250 1.1442 0.09850 0.09573 -0.0375 0.0029 1.0000
15.500 1.1215 0.10859 0.10597 -0.0434 0.0029 1.0000
15.750 1.0975 0.11953 0.11706 -0.0498 0.0029 1.0000
16.000 1.0677 0.13247 0.13017 -0.0572 0.0031 1.0000
16.250 1.0351 0.14710 0.14495 -0.0654 0.0032 1.0000
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Polar data table (+)
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