RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Reynolds number: 500,000 Max Cl/Cd: 67.79 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg14a147-il-500000-n5.txt Download as CSV file: xf-rg14a147-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RG 14A-1.4/7.0 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5272 0.08306 0.08084 -0.0150 1.0000 0.0053
-8.250 -0.5317 0.07855 0.07637 -0.0174 1.0000 0.0051
-8.000 -0.5510 0.07121 0.06909 -0.0226 1.0000 0.0044
-7.750 -0.5433 0.06968 0.06755 -0.0240 1.0000 0.0053
-7.500 -0.5417 0.06519 0.06304 -0.0272 1.0000 0.0057
-7.250 -0.5412 0.05957 0.05735 -0.0301 1.0000 0.0055
-7.000 -0.5359 0.05501 0.05270 -0.0316 1.0000 0.0060
-6.750 -0.5299 0.05009 0.04765 -0.0324 1.0000 0.0062
-6.500 -0.5232 0.04489 0.04226 -0.0324 1.0000 0.0060
-6.250 -0.5147 0.03984 0.03697 -0.0317 1.0000 0.0059
-6.000 -0.5055 0.03439 0.03120 -0.0303 1.0000 0.0055
-5.750 -0.4956 0.02816 0.02449 -0.0280 1.0000 0.0051
-5.500 -0.4797 0.02174 0.01735 -0.0261 0.9994 0.0046
-5.250 -0.4498 0.01803 0.01305 -0.0267 0.9970 0.0044
-5.000 -0.4184 0.01585 0.01043 -0.0275 0.9947 0.0044
-4.750 -0.3878 0.01415 0.00844 -0.0281 0.9921 0.0045
-4.500 -0.3571 0.01287 0.00697 -0.0288 0.9889 0.0046
-4.250 -0.3253 0.01185 0.00581 -0.0297 0.9857 0.0049
-4.000 -0.2921 0.01102 0.00487 -0.0309 0.9829 0.0054
-3.750 -0.2614 0.01037 0.00413 -0.0315 0.9786 0.0065
-3.500 -0.2301 0.00989 0.00357 -0.0322 0.9736 0.0080
-3.250 -0.1965 0.00938 0.00302 -0.0335 0.9697 0.0115
-3.000 -0.1664 0.00903 0.00256 -0.0339 0.9628 0.0150
-2.750 -0.1336 0.00859 0.00219 -0.0351 0.9567 0.0349
-2.500 -0.1027 0.00822 0.00194 -0.0358 0.9482 0.0702
-2.250 -0.0699 0.00782 0.00172 -0.0370 0.9395 0.1266
-2.000 -0.0381 0.00725 0.00152 -0.0382 0.9284 0.2364
-1.750 -0.0079 0.00675 0.00136 -0.0389 0.9139 0.3467
-1.500 0.0210 0.00642 0.00120 -0.0393 0.8964 0.4277
-1.250 0.0474 0.00597 0.00108 -0.0390 0.8764 0.5476
-1.000 0.0697 0.00541 0.00105 -0.0378 0.8538 0.7150
-0.750 0.0929 0.00527 0.00108 -0.0364 0.8298 0.8036
-0.500 0.1175 0.00528 0.00107 -0.0354 0.8036 0.8386
-0.250 0.1423 0.00533 0.00104 -0.0344 0.7771 0.8622
0.000 0.1668 0.00540 0.00104 -0.0334 0.7548 0.8837
0.250 0.1917 0.00547 0.00105 -0.0325 0.7349 0.9019
0.500 0.2168 0.00554 0.00107 -0.0317 0.7126 0.9189
0.750 0.2428 0.00562 0.00108 -0.0310 0.6818 0.9353
1.000 0.2703 0.00575 0.00109 -0.0308 0.6488 0.9502
1.250 0.3011 0.00590 0.00112 -0.0314 0.6176 0.9640
1.500 0.3344 0.00607 0.00116 -0.0326 0.5832 0.9755
1.750 0.3679 0.00626 0.00122 -0.0339 0.5461 0.9846
2.000 0.4016 0.00648 0.00129 -0.0353 0.5059 0.9915
2.250 0.4344 0.00671 0.00136 -0.0366 0.4656 0.9973
2.500 0.4616 0.00695 0.00146 -0.0367 0.4270 1.0000
2.750 0.4840 0.00720 0.00160 -0.0357 0.3896 1.0000
3.000 0.5066 0.00750 0.00174 -0.0347 0.3480 1.0000
3.250 0.5297 0.00782 0.00190 -0.0339 0.3049 1.0000
3.500 0.5532 0.00816 0.00208 -0.0332 0.2628 1.0000
3.750 0.5757 0.00868 0.00232 -0.0324 0.1982 1.0000
4.250 0.6222 0.00970 0.00292 -0.0311 0.0982 1.0000
4.500 0.6464 0.01011 0.00322 -0.0306 0.0706 1.0000
4.750 0.6707 0.01054 0.00355 -0.0301 0.0468 1.0000
5.000 0.6951 0.01098 0.00392 -0.0296 0.0281 1.0000
5.250 0.7199 0.01139 0.00432 -0.0291 0.0200 1.0000
5.500 0.7444 0.01185 0.00480 -0.0285 0.0162 1.0000
5.750 0.7681 0.01248 0.00558 -0.0277 0.0140 1.0000
6.000 0.7924 0.01299 0.00617 -0.0271 0.0134 1.0000
6.250 0.8177 0.01327 0.00654 -0.0268 0.0118 1.0000
6.500 0.8425 0.01363 0.00696 -0.0264 0.0100 1.0000
6.750 0.8662 0.01420 0.00758 -0.0258 0.0087 1.0000
7.000 0.8882 0.01506 0.00857 -0.0250 0.0072 1.0000
7.250 0.9120 0.01559 0.00920 -0.0244 0.0062 1.0000
7.500 0.9346 0.01634 0.01005 -0.0236 0.0049 1.0000
7.750 0.9582 0.01686 0.01063 -0.0231 0.0041 1.0000
8.000 0.9779 0.01804 0.01192 -0.0220 0.0031 1.0000
8.250 0.9992 0.01897 0.01304 -0.0211 0.0029 1.0000
8.500 1.0194 0.02006 0.01431 -0.0201 0.0026 1.0000
8.750 1.0379 0.02147 0.01593 -0.0188 0.0024 1.0000
9.000 1.0559 0.02291 0.01759 -0.0176 0.0023 1.0000
9.250 1.0732 0.02440 0.01930 -0.0163 0.0020 1.0000
9.500 1.0885 0.02614 0.02129 -0.0149 0.0019 1.0000
9.750 1.1035 0.02774 0.02312 -0.0136 0.0017 1.0000
10.000 1.1148 0.02978 0.02543 -0.0119 0.0017 1.0000
10.250 1.1263 0.03149 0.02735 -0.0104 0.0015 1.0000
10.500 1.1294 0.03415 0.03032 -0.0081 0.0015 1.0000
10.750 1.1259 0.03717 0.03367 -0.0054 0.0015 1.0000
11.000 1.1138 0.04005 0.03680 -0.0017 0.0014 1.0000
11.250 1.0981 0.04330 0.04030 0.0009 0.0014 1.0000
11.500 1.0772 0.04755 0.04477 0.0017 0.0014 1.0000
11.750 1.0589 0.05251 0.04993 0.0002 0.0014 1.0000
12.000 1.0377 0.05929 0.05691 -0.0040 0.0014 1.0000
12.250 1.0176 0.06793 0.06571 -0.0107 0.0014 1.0000
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Polar data table (+)
Polar graphs
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