RG-15 8.9% (rg15-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG-15 8.9% (rg15-il) Reynolds number: 50,000 Max Cl/Cd: 34.85 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg15-il-50000.txt Download as CSV file: xf-rg15-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4551 0.10813 0.10116 -0.0106 1.0000 0.2451
-8.750 -0.4522 0.10499 0.09802 -0.0103 1.0000 0.2586
-8.500 -0.4753 0.10441 0.09767 -0.0119 1.0000 0.2667
-8.250 -0.4500 0.09899 0.09217 -0.0097 1.0000 0.2843
-7.750 -0.4457 0.09289 0.08620 -0.0083 1.0000 0.3123
-7.500 -0.4400 0.08960 0.08297 -0.0071 1.0000 0.3281
-7.250 -0.4364 0.08663 0.08006 -0.0058 1.0000 0.3437
-7.000 -0.4371 0.08396 0.07747 -0.0042 1.0000 0.3617
-6.750 -0.4548 0.08257 0.07627 -0.0019 1.0000 0.3799
-6.500 -0.4435 0.07936 0.07308 0.0008 1.0000 0.4069
-5.750 -0.4834 0.05057 0.04338 -0.0388 1.0000 0.1369
-5.500 -0.4683 0.04515 0.03733 -0.0397 1.0000 0.1238
-5.250 -0.4508 0.04081 0.03247 -0.0395 1.0000 0.1183
-5.000 -0.4313 0.03732 0.02846 -0.0390 1.0000 0.1190
-4.750 -0.4099 0.03442 0.02501 -0.0384 1.0000 0.1239
-4.500 -0.3860 0.03155 0.02152 -0.0375 1.0000 0.1258
-4.250 -0.3621 0.02892 0.01862 -0.0366 1.0000 0.1300
-4.000 -0.3374 0.02700 0.01631 -0.0355 1.0000 0.1403
-3.750 -0.3146 0.02517 0.01457 -0.0344 1.0000 0.1589
-3.500 -0.2901 0.02338 0.01273 -0.0328 1.0000 0.1833
-3.250 -0.2680 0.02154 0.01131 -0.0314 1.0000 0.2443
-3.000 -0.2517 0.01834 0.00993 -0.0290 1.0000 0.4762
-2.750 -0.2623 0.01773 0.01067 -0.0168 1.0000 0.7758
-2.500 -0.1054 0.01826 0.00995 -0.0327 1.0000 1.0000
-2.250 -0.1096 0.01785 0.00944 -0.0290 1.0000 1.0000
-2.000 -0.1136 0.01752 0.00899 -0.0251 1.0000 1.0000
-1.750 -0.1143 0.01727 0.00856 -0.0216 1.0000 1.0000
-1.500 -0.1065 0.01715 0.00822 -0.0194 1.0000 1.0000
-1.250 -0.0923 0.01715 0.00799 -0.0183 1.0000 1.0000
-1.000 -0.0749 0.01724 0.00784 -0.0175 1.0000 1.0000
-0.750 -0.0561 0.01739 0.00779 -0.0170 1.0000 1.0000
-0.500 -0.0367 0.01760 0.00778 -0.0166 1.0000 1.0000
-0.250 -0.0172 0.01787 0.00788 -0.0163 1.0000 1.0000
0.000 0.0023 0.01818 0.00805 -0.0160 1.0000 1.0000
0.250 0.0216 0.01856 0.00829 -0.0157 1.0000 1.0000
0.500 0.0406 0.01899 0.00861 -0.0155 1.0000 1.0000
0.750 0.0593 0.01947 0.00899 -0.0154 1.0000 1.0000
1.000 0.0776 0.02002 0.00947 -0.0153 1.0000 1.0000
1.250 0.0955 0.02063 0.01002 -0.0152 1.0000 1.0000
1.500 0.1129 0.02132 0.01067 -0.0153 1.0000 1.0000
1.750 0.1300 0.02208 0.01139 -0.0154 1.0000 1.0000
2.000 0.1882 0.02352 0.01284 -0.0231 0.9801 1.0000
2.250 0.2466 0.02471 0.01408 -0.0303 0.9581 1.0000
2.500 0.2989 0.02560 0.01507 -0.0360 0.9348 1.0000
2.750 0.3532 0.02634 0.01592 -0.0416 0.9117 1.0000
3.000 0.4096 0.02682 0.01660 -0.0470 0.8883 1.0000
3.250 0.4573 0.02712 0.01708 -0.0505 0.8631 1.0000
3.500 0.5088 0.02717 0.01734 -0.0541 0.8378 1.0000
3.750 0.5652 0.02685 0.01733 -0.0576 0.8127 1.0000
4.000 0.6178 0.02627 0.01701 -0.0598 0.7866 1.0000
4.250 0.6628 0.02567 0.01665 -0.0603 0.7579 1.0000
4.500 0.7019 0.02512 0.01636 -0.0597 0.7266 1.0000
4.750 0.7405 0.02445 0.01585 -0.0585 0.6932 1.0000
5.000 0.7690 0.02426 0.01576 -0.0563 0.6555 1.0000
5.250 0.7967 0.02411 0.01565 -0.0539 0.6150 1.0000
5.500 0.8217 0.02414 0.01566 -0.0513 0.5710 1.0000
5.750 0.8457 0.02431 0.01576 -0.0486 0.5239 1.0000
6.000 0.8649 0.02482 0.01617 -0.0458 0.4723 1.0000
6.250 0.8836 0.02552 0.01667 -0.0429 0.4183 1.0000
6.500 0.9010 0.02650 0.01740 -0.0402 0.3633 1.0000
6.750 0.9179 0.02778 0.01838 -0.0377 0.3107 1.0000
7.000 0.9349 0.02940 0.01981 -0.0355 0.2635 1.0000
7.250 0.9523 0.03118 0.02150 -0.0335 0.2234 1.0000
7.500 0.9728 0.03341 0.02361 -0.0320 0.1918 1.0000
7.750 0.9919 0.03589 0.02617 -0.0304 0.1662 1.0000
8.000 1.0096 0.03853 0.02889 -0.0288 0.1447 1.0000
8.250 1.0262 0.04175 0.03243 -0.0270 0.1291 1.0000
8.500 1.0392 0.04471 0.03564 -0.0251 0.1146 1.0000
8.750 1.0533 0.04876 0.03991 -0.0235 0.1065 1.0000
9.000 1.0567 0.05244 0.04419 -0.0210 0.1003 1.0000
9.250 1.0648 0.05618 0.04807 -0.0195 0.0936 1.0000
9.500 1.0600 0.06079 0.05321 -0.0172 0.0926 1.0000
9.750 1.0518 0.06554 0.05838 -0.0152 0.0926 1.0000
10.000 1.0389 0.07037 0.06354 -0.0136 0.0930 1.0000
10.250 1.0242 0.07515 0.06854 -0.0123 0.0937 1.0000
10.500 1.0082 0.07980 0.07332 -0.0112 0.0944 1.0000
10.750 0.9955 0.08493 0.07854 -0.0111 0.0951 1.0000
11.000 0.9190 0.09507 0.08890 -0.0192 0.1062 1.0000
11.250 0.9066 0.10230 0.09611 -0.0227 0.1076 1.0000
11.500 0.9004 0.10925 0.10305 -0.0256 0.1084 1.0000
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Polar data table (+)
Polar graphs
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