RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 10% AIRFOIL (rg1410-il) Reynolds number: 100,000 Max Cl/Cd: 48.22 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg1410-il-100000.txt Download as CSV file: xf-rg1410-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 10% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4846 0.10302 0.09782 -0.0199 1.0000 0.1257
-9.500 -0.5013 0.09960 0.09450 -0.0241 1.0000 0.1311
-9.250 -0.5466 0.09553 0.09063 -0.0329 1.0000 0.1324
-9.000 -0.4925 0.09185 0.08682 -0.0239 1.0000 0.1371
-8.750 -0.4935 0.08856 0.08358 -0.0246 1.0000 0.1423
-8.500 -0.5428 0.08449 0.07970 -0.0316 1.0000 0.1463
-8.250 -0.5347 0.08010 0.07536 -0.0300 1.0000 0.1492
-8.000 -0.5188 0.07758 0.07285 -0.0273 1.0000 0.1544
-7.750 -0.5869 0.07410 0.06920 -0.0336 1.0000 0.1616
-7.500 -0.5505 0.06953 0.06486 -0.0298 1.0000 0.1648
-7.250 -0.6061 0.05137 0.04565 -0.0357 1.0000 0.0917
-7.000 -0.6082 0.04406 0.03760 -0.0332 1.0000 0.0751
-6.750 -0.6007 0.04048 0.03370 -0.0311 1.0000 0.0747
-6.500 -0.5913 0.03730 0.03008 -0.0289 1.0000 0.0751
-6.250 -0.5790 0.03419 0.02656 -0.0268 1.0000 0.0749
-6.000 -0.5642 0.03137 0.02331 -0.0248 1.0000 0.0749
-5.750 -0.5471 0.02905 0.02054 -0.0229 1.0000 0.0756
-5.500 -0.5292 0.02675 0.01801 -0.0215 1.0000 0.0787
-5.250 -0.5096 0.02534 0.01649 -0.0201 1.0000 0.0829
-5.000 -0.4885 0.02381 0.01471 -0.0187 1.0000 0.0863
-4.750 -0.4668 0.02247 0.01307 -0.0172 1.0000 0.0904
-4.500 -0.4463 0.02124 0.01196 -0.0161 1.0000 0.0992
-4.250 -0.4252 0.02005 0.01077 -0.0148 1.0000 0.1089
-4.000 -0.4045 0.01902 0.00979 -0.0134 1.0000 0.1239
-3.750 -0.3845 0.01810 0.00899 -0.0121 1.0000 0.1494
-3.500 -0.3653 0.01722 0.00836 -0.0108 1.0000 0.1880
-3.250 -0.3467 0.01632 0.00786 -0.0095 1.0000 0.2487
-3.000 -0.3297 0.01526 0.00750 -0.0081 1.0000 0.3569
-2.750 -0.3161 0.01416 0.00741 -0.0055 1.0000 0.5392
-2.500 -0.3070 0.01373 0.00789 -0.0003 1.0000 0.7447
-2.250 -0.2958 0.01395 0.00826 0.0044 1.0000 0.8604
-2.000 -0.2404 0.01448 0.00866 0.0010 1.0000 0.9508
-1.750 -0.1022 0.01511 0.00877 -0.0189 1.0000 1.0000
-1.500 -0.1097 0.01504 0.00864 -0.0143 1.0000 1.0000
-1.250 -0.1144 0.01503 0.00855 -0.0102 1.0000 1.0000
-1.000 -0.0923 0.01524 0.00863 -0.0107 0.9960 1.0000
-0.750 -0.0385 0.01563 0.00886 -0.0166 0.9855 1.0000
-0.500 0.0131 0.01591 0.00901 -0.0220 0.9742 1.0000
-0.250 0.0635 0.01610 0.00910 -0.0269 0.9623 1.0000
0.000 0.1129 0.01621 0.00914 -0.0316 0.9503 1.0000
0.250 0.1648 0.01625 0.00913 -0.0365 0.9389 1.0000
0.500 0.2216 0.01618 0.00903 -0.0421 0.9288 1.0000
0.750 0.2709 0.01603 0.00888 -0.0462 0.9160 1.0000
1.000 0.3223 0.01580 0.00867 -0.0505 0.9035 1.0000
1.250 0.3707 0.01548 0.00838 -0.0540 0.8900 1.0000
1.500 0.4149 0.01515 0.00808 -0.0566 0.8750 1.0000
1.750 0.4543 0.01482 0.00778 -0.0581 0.8581 1.0000
2.000 0.4910 0.01446 0.00743 -0.0588 0.8394 1.0000
2.250 0.5154 0.01429 0.00727 -0.0572 0.8151 1.0000
2.500 0.5418 0.01409 0.00704 -0.0559 0.7915 1.0000
2.750 0.5644 0.01399 0.00690 -0.0540 0.7658 1.0000
3.000 0.5851 0.01401 0.00688 -0.0520 0.7400 1.0000
3.250 0.6070 0.01406 0.00690 -0.0502 0.7153 1.0000
3.500 0.6286 0.01415 0.00693 -0.0484 0.6902 1.0000
3.750 0.6484 0.01431 0.00705 -0.0463 0.6633 1.0000
4.000 0.6684 0.01448 0.00715 -0.0443 0.6352 1.0000
4.250 0.6879 0.01466 0.00728 -0.0422 0.6054 1.0000
4.500 0.7070 0.01488 0.00741 -0.0400 0.5740 1.0000
4.750 0.7258 0.01514 0.00756 -0.0379 0.5413 1.0000
5.000 0.7441 0.01545 0.00778 -0.0357 0.5061 1.0000
5.250 0.7619 0.01580 0.00803 -0.0335 0.4678 1.0000
5.500 0.7789 0.01623 0.00833 -0.0312 0.4254 1.0000
5.750 0.7951 0.01680 0.00869 -0.0289 0.3790 1.0000
6.000 0.8108 0.01753 0.00916 -0.0267 0.3323 1.0000
6.250 0.8270 0.01837 0.00978 -0.0246 0.2897 1.0000
6.500 0.8441 0.01930 0.01049 -0.0228 0.2547 1.0000
6.750 0.8620 0.02028 0.01130 -0.0212 0.2255 1.0000
7.000 0.8805 0.02131 0.01217 -0.0198 0.2012 1.0000
7.250 0.9001 0.02242 0.01322 -0.0185 0.1805 1.0000
7.500 0.9202 0.02360 0.01436 -0.0173 0.1631 1.0000
7.750 0.9412 0.02491 0.01563 -0.0163 0.1482 1.0000
8.000 0.9623 0.02630 0.01705 -0.0154 0.1352 1.0000
8.250 0.9837 0.02780 0.01857 -0.0145 0.1239 1.0000
8.500 1.0055 0.02936 0.02006 -0.0138 0.1138 1.0000
8.750 1.0245 0.03068 0.02167 -0.0124 0.1051 1.0000
9.000 1.0437 0.03247 0.02360 -0.0113 0.0972 1.0000
9.250 1.0632 0.03403 0.02521 -0.0103 0.0902 1.0000
9.500 1.0778 0.03627 0.02780 -0.0086 0.0841 1.0000
9.750 1.0939 0.03794 0.02960 -0.0072 0.0782 1.0000
10.000 1.1053 0.04072 0.03268 -0.0055 0.0737 1.0000
10.250 1.1115 0.04315 0.03556 -0.0030 0.0696 1.0000
10.500 1.1246 0.04515 0.03762 -0.0016 0.0655 1.0000
10.750 1.1278 0.04877 0.04147 0.0003 0.0628 1.0000
11.000 1.1182 0.05180 0.04502 0.0038 0.0613 1.0000
11.250 1.1046 0.05520 0.04883 0.0072 0.0602 1.0000
11.500 1.0861 0.05862 0.05255 0.0107 0.0599 1.0000
11.750 1.0638 0.06241 0.05661 0.0131 0.0598 1.0000
12.000 1.0397 0.06675 0.06118 0.0142 0.0601 1.0000
12.250 1.0130 0.07185 0.06649 0.0136 0.0606 1.0000
12.500 0.9852 0.07791 0.07272 0.0113 0.0612 1.0000
12.750 0.9581 0.08499 0.07993 0.0075 0.0619 1.0000
13.000 0.9325 0.09306 0.08807 0.0028 0.0627 1.0000
13.250 0.9111 0.10162 0.09667 -0.0020 0.0634 1.0000
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Polar data table (+)
Polar graphs
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