RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 9.5% AIRFOIL (rg1495-il) Reynolds number: 50,000 Max Cl/Cd: 32.68 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg1495-il-50000.txt Download as CSV file: xf-rg1495-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 9.5% AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5142 0.13070 0.12334 -0.0068 1.0000 0.2162
-10.500 -0.4861 0.12422 0.11678 -0.0052 1.0000 0.2247
-10.250 -0.5119 0.12418 0.11690 -0.0080 1.0000 0.2311
-10.000 -0.4883 0.11864 0.11131 -0.0065 1.0000 0.2441
-9.750 -0.4759 0.11445 0.10714 -0.0059 1.0000 0.2555
-9.500 -0.4739 0.11111 0.10384 -0.0061 1.0000 0.2654
-9.250 -0.4958 0.11042 0.10329 -0.0076 1.0000 0.2753
-9.000 -0.4778 0.10580 0.09866 -0.0064 1.0000 0.2889
-8.750 -0.4628 0.10144 0.09430 -0.0056 1.0000 0.2996
-8.500 -0.4597 0.09814 0.09105 -0.0053 1.0000 0.3112
-8.250 -0.4601 0.09516 0.08815 -0.0050 1.0000 0.3238
-8.000 -0.4568 0.09208 0.08512 -0.0042 1.0000 0.3386
-7.750 -0.4488 0.08901 0.08206 -0.0028 1.0000 0.3586
-7.500 -0.4570 0.08693 0.08009 -0.0014 1.0000 0.3779
-6.750 -0.5519 0.06171 0.05482 -0.0298 1.0000 0.1691
-6.500 -0.5578 0.05421 0.04677 -0.0317 1.0000 0.1454
-6.250 -0.5480 0.04983 0.04210 -0.0310 1.0000 0.1384
-6.000 -0.5389 0.04567 0.03754 -0.0300 1.0000 0.1355
-5.750 -0.5268 0.04214 0.03360 -0.0288 1.0000 0.1360
-5.500 -0.5120 0.03884 0.02984 -0.0274 1.0000 0.1367
-5.250 -0.4946 0.03574 0.02625 -0.0261 1.0000 0.1370
-5.000 -0.4749 0.03301 0.02303 -0.0247 1.0000 0.1394
-4.750 -0.4547 0.03075 0.02043 -0.0234 1.0000 0.1468
-4.500 -0.4329 0.02888 0.01818 -0.0220 1.0000 0.1568
-4.250 -0.4101 0.02692 0.01616 -0.0208 1.0000 0.1685
-4.000 -0.3879 0.02529 0.01450 -0.0194 1.0000 0.1905
-3.750 -0.3655 0.02371 0.01306 -0.0180 1.0000 0.2235
-3.500 -0.3436 0.02214 0.01181 -0.0166 1.0000 0.2813
-3.250 -0.3243 0.02032 0.01066 -0.0147 1.0000 0.3844
-3.000 -0.3176 0.01807 0.01018 -0.0089 1.0000 0.6133
-2.750 -0.0995 0.01905 0.01035 -0.0337 1.0000 1.0000
-2.500 -0.0994 0.01867 0.00983 -0.0305 1.0000 1.0000
-2.250 -0.0984 0.01841 0.00944 -0.0271 1.0000 1.0000
-2.000 -0.0970 0.01823 0.00912 -0.0236 1.0000 1.0000
-1.750 -0.0951 0.01813 0.00888 -0.0201 1.0000 1.0000
-1.500 -0.0922 0.01807 0.00870 -0.0167 1.0000 1.0000
-1.250 -0.0875 0.01808 0.00857 -0.0136 1.0000 1.0000
-1.000 -0.0811 0.01814 0.00849 -0.0109 1.0000 1.0000
-0.750 -0.0722 0.01826 0.00848 -0.0085 1.0000 1.0000
-0.500 -0.0612 0.01845 0.00851 -0.0066 1.0000 1.0000
-0.250 -0.0487 0.01869 0.00863 -0.0050 1.0000 1.0000
0.000 -0.0352 0.01900 0.00882 -0.0037 1.0000 1.0000
0.250 -0.0210 0.01935 0.00908 -0.0026 1.0000 1.0000
0.500 -0.0063 0.01977 0.00940 -0.0016 1.0000 1.0000
0.750 0.0085 0.02025 0.00980 -0.0008 1.0000 1.0000
1.000 0.0234 0.02079 0.01028 -0.0002 1.0000 1.0000
1.250 0.0383 0.02140 0.01084 0.0003 1.0000 1.0000
1.500 0.0572 0.02213 0.01154 -0.0001 0.9982 1.0000
1.750 0.1179 0.02354 0.01294 -0.0082 0.9773 1.0000
2.000 0.1787 0.02478 0.01422 -0.0158 0.9567 1.0000
2.250 0.2277 0.02562 0.01513 -0.0210 0.9339 1.0000
2.500 0.2848 0.02641 0.01602 -0.0271 0.9123 1.0000
2.750 0.3312 0.02697 0.01671 -0.0310 0.8887 1.0000
3.000 0.3827 0.02739 0.01728 -0.0353 0.8660 1.0000
3.250 0.4373 0.02754 0.01762 -0.0396 0.8426 1.0000
3.500 0.4893 0.02744 0.01776 -0.0428 0.8171 1.0000
3.750 0.5474 0.02661 0.01717 -0.0455 0.7883 1.0000
4.000 0.5977 0.02562 0.01642 -0.0462 0.7579 1.0000
4.250 0.6373 0.02499 0.01596 -0.0456 0.7281 1.0000
4.500 0.6726 0.02446 0.01555 -0.0443 0.6965 1.0000
4.750 0.7040 0.02400 0.01518 -0.0422 0.6613 1.0000
5.000 0.7302 0.02373 0.01491 -0.0394 0.6208 1.0000
5.250 0.7543 0.02356 0.01463 -0.0363 0.5747 1.0000
5.500 0.7728 0.02379 0.01474 -0.0330 0.5224 1.0000
5.750 0.7916 0.02422 0.01494 -0.0298 0.4669 1.0000
6.000 0.8103 0.02496 0.01533 -0.0270 0.4132 1.0000
6.250 0.8275 0.02604 0.01620 -0.0245 0.3650 1.0000
6.500 0.8468 0.02726 0.01714 -0.0225 0.3240 1.0000
6.750 0.8655 0.02870 0.01855 -0.0206 0.2888 1.0000
7.000 0.8857 0.03028 0.02006 -0.0191 0.2597 1.0000
7.250 0.9067 0.03200 0.02169 -0.0178 0.2352 1.0000
7.500 0.9265 0.03395 0.02376 -0.0163 0.2148 1.0000
7.750 0.9476 0.03594 0.02570 -0.0152 0.1967 1.0000
8.000 0.9671 0.03831 0.02825 -0.0139 0.1823 1.0000
8.250 0.9824 0.04087 0.03114 -0.0122 0.1699 1.0000
8.500 0.9934 0.04389 0.03458 -0.0102 0.1601 1.0000
8.750 1.0106 0.04714 0.03792 -0.0091 0.1519 1.0000
9.000 1.0098 0.05075 0.04219 -0.0063 0.1463 1.0000
9.250 1.0277 0.05406 0.04543 -0.0055 0.1382 1.0000
9.500 1.0195 0.05849 0.05046 -0.0028 0.1368 1.0000
9.750 1.0066 0.06315 0.05557 -0.0006 0.1361 1.0000
10.000 0.9895 0.06798 0.06073 0.0012 0.1361 1.0000
10.250 0.9690 0.07295 0.06591 0.0025 0.1366 1.0000
10.500 0.9476 0.07786 0.07094 0.0035 0.1375 1.0000
10.750 0.9287 0.08330 0.07643 0.0033 0.1383 1.0000
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Polar data table (+)
Polar graphs
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