RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 AIRFOIL (rg14-il) Reynolds number: 100,000 Max Cl/Cd: 49.18 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg14-il-100000.txt Download as CSV file: xf-rg14-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4867 0.10303 0.09801 -0.0162 1.0000 0.0917
-9.000 -0.4925 0.09970 0.09476 -0.0191 1.0000 0.0956
-8.750 -0.5165 0.09663 0.09183 -0.0261 1.0000 0.0973
-8.500 -0.5031 0.09172 0.08694 -0.0236 1.0000 0.0995
-8.250 -0.4912 0.08857 0.08379 -0.0217 1.0000 0.1029
-8.000 -0.4950 0.08524 0.08053 -0.0231 1.0000 0.1067
-7.750 -0.5189 0.08140 0.07678 -0.0292 1.0000 0.1100
-7.500 -0.5332 0.07669 0.07205 -0.0330 1.0000 0.1120
-7.250 -0.5141 0.07366 0.06912 -0.0285 1.0000 0.1156
-7.000 -0.5148 0.07020 0.06565 -0.0296 1.0000 0.1211
-6.750 -0.5220 0.06580 0.06117 -0.0318 1.0000 0.1269
-6.500 -0.5121 0.06283 0.05824 -0.0301 1.0000 0.1315
-6.250 -0.5136 0.05891 0.05417 -0.0312 1.0000 0.1409
-6.000 -0.5035 0.05596 0.05122 -0.0298 1.0000 0.1467
-5.750 -0.4977 0.04242 0.03630 -0.0330 1.0000 0.0728
-5.500 -0.4820 0.03678 0.03001 -0.0309 1.0000 0.0560
-5.250 -0.4666 0.03344 0.02628 -0.0294 1.0000 0.0554
-5.000 -0.4488 0.03074 0.02307 -0.0277 1.0000 0.0564
-4.750 -0.4292 0.02810 0.01993 -0.0260 1.0000 0.0569
-4.500 -0.4080 0.02553 0.01696 -0.0245 1.0000 0.0567
-4.250 -0.3853 0.02353 0.01454 -0.0230 1.0000 0.0577
-4.000 -0.3627 0.02111 0.01205 -0.0219 1.0000 0.0611
-3.750 -0.3399 0.01974 0.01055 -0.0205 1.0000 0.0692
-3.500 -0.3185 0.01833 0.00918 -0.0193 1.0000 0.0879
-3.250 -0.2974 0.01713 0.00813 -0.0181 1.0000 0.1225
-3.000 -0.2767 0.01585 0.00718 -0.0168 1.0000 0.1793
-2.750 -0.2584 0.01410 0.00650 -0.0156 1.0000 0.3371
-2.500 -0.2500 0.01248 0.00662 -0.0108 1.0000 0.6931
-2.250 -0.2360 0.01250 0.00699 -0.0053 1.0000 0.9002
-2.000 -0.1056 0.01281 0.00660 -0.0236 1.0000 1.0000
-1.750 -0.1048 0.01273 0.00640 -0.0196 1.0000 1.0000
-1.500 -0.1013 0.01271 0.00625 -0.0161 1.0000 1.0000
-1.250 -0.0939 0.01275 0.00616 -0.0133 1.0000 1.0000
-1.000 -0.0824 0.01287 0.00614 -0.0112 1.0000 1.0000
-0.750 -0.0683 0.01305 0.00618 -0.0097 1.0000 1.0000
-0.500 -0.0529 0.01329 0.00627 -0.0084 1.0000 1.0000
-0.250 -0.0234 0.01366 0.00652 -0.0099 0.9961 1.0000
0.000 0.0297 0.01414 0.00687 -0.0157 0.9846 1.0000
0.250 0.0809 0.01449 0.00712 -0.0209 0.9724 1.0000
0.500 0.1317 0.01473 0.00730 -0.0259 0.9596 1.0000
0.750 0.1820 0.01486 0.00741 -0.0306 0.9463 1.0000
1.000 0.2322 0.01489 0.00743 -0.0351 0.9329 1.0000
1.250 0.2835 0.01481 0.00738 -0.0396 0.9196 1.0000
1.500 0.3371 0.01460 0.00724 -0.0443 0.9065 1.0000
1.750 0.3867 0.01431 0.00702 -0.0480 0.8918 1.0000
2.000 0.4331 0.01398 0.00675 -0.0508 0.8757 1.0000
2.250 0.4695 0.01374 0.00657 -0.0516 0.8551 1.0000
2.500 0.5047 0.01350 0.00640 -0.0520 0.8338 1.0000
2.750 0.5323 0.01339 0.00631 -0.0510 0.8083 1.0000
3.000 0.5583 0.01335 0.00627 -0.0498 0.7815 1.0000
3.250 0.5829 0.01336 0.00626 -0.0482 0.7531 1.0000
3.500 0.6068 0.01343 0.00633 -0.0466 0.7234 1.0000
3.750 0.6291 0.01357 0.00643 -0.0448 0.6912 1.0000
4.000 0.6512 0.01375 0.00656 -0.0430 0.6576 1.0000
4.250 0.6731 0.01398 0.00671 -0.0412 0.6227 1.0000
4.500 0.6945 0.01426 0.00691 -0.0395 0.5858 1.0000
4.750 0.7154 0.01458 0.00722 -0.0377 0.5467 1.0000
5.000 0.7358 0.01496 0.00750 -0.0359 0.5056 1.0000
5.250 0.7558 0.01540 0.00783 -0.0341 0.4627 1.0000
5.500 0.7751 0.01592 0.00821 -0.0323 0.4175 1.0000
5.750 0.7937 0.01652 0.00868 -0.0305 0.3684 1.0000
6.000 0.8116 0.01726 0.00923 -0.0286 0.3179 1.0000
6.250 0.8287 0.01817 0.00990 -0.0268 0.2678 1.0000
6.500 0.8455 0.01923 0.01082 -0.0250 0.2183 1.0000
6.750 0.8620 0.02047 0.01184 -0.0233 0.1756 1.0000
7.000 0.8785 0.02186 0.01306 -0.0216 0.1390 1.0000
7.250 0.8951 0.02334 0.01440 -0.0200 0.1093 1.0000
7.500 0.9133 0.02535 0.01635 -0.0183 0.0882 1.0000
7.750 0.9310 0.02700 0.01799 -0.0169 0.0709 1.0000
8.000 0.9521 0.02951 0.02063 -0.0156 0.0604 1.0000
8.250 0.9705 0.03182 0.02306 -0.0143 0.0514 1.0000
8.500 0.9897 0.03410 0.02555 -0.0130 0.0460 1.0000
8.750 1.0075 0.03882 0.03048 -0.0121 0.0433 1.0000
9.000 1.0191 0.04196 0.03420 -0.0099 0.0426 1.0000
9.250 1.0256 0.04541 0.03823 -0.0074 0.0417 1.0000
9.500 1.0282 0.04916 0.04247 -0.0050 0.0413 1.0000
9.750 1.0246 0.05273 0.04652 -0.0023 0.0402 1.0000
10.000 1.0169 0.05665 0.05081 0.0001 0.0401 1.0000
10.250 1.0037 0.06046 0.05494 0.0025 0.0401 1.0000
10.500 0.9862 0.06412 0.05882 0.0049 0.0405 1.0000
10.750 0.9671 0.06820 0.06307 0.0059 0.0410 1.0000
11.000 0.9454 0.07284 0.06788 0.0053 0.0412 1.0000
11.250 0.9272 0.07821 0.07336 0.0033 0.0420 1.0000
11.500 0.9060 0.08444 0.07970 -0.0004 0.0423 1.0000
11.750 0.8958 0.09090 0.08617 -0.0029 0.0432 1.0000
12.000 0.7272 0.10750 0.10321 -0.0153 0.0532 1.0000
12.250 0.7193 0.11376 0.10946 -0.0174 0.0543 1.0000
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Polar data table (+)
Polar graphs
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