RG 14 9.5% AIRFOIL (rg1495-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 9.5% AIRFOIL (rg1495-il) Reynolds number: 200,000 Max Cl/Cd: 57.91 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg1495-il-200000-n5.txt Download as CSV file: xf-rg1495-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5691 0.08176 0.07813 -0.0304 1.0000 0.0168
-10.000 -0.5896 0.07308 0.06952 -0.0356 1.0000 0.0162
-9.750 -0.6544 0.05455 0.05087 -0.0491 1.0000 0.0151
-9.500 -0.6932 0.04833 0.04439 -0.0476 1.0000 0.0149
-9.250 -0.7139 0.04322 0.03894 -0.0454 1.0000 0.0149
-9.000 -0.7203 0.03958 0.03497 -0.0432 1.0000 0.0153
-8.750 -0.7212 0.03628 0.03130 -0.0408 1.0000 0.0159
-8.500 -0.7178 0.03330 0.02788 -0.0384 1.0000 0.0169
-8.250 -0.7110 0.03054 0.02460 -0.0360 1.0000 0.0177
-8.000 -0.7012 0.02805 0.02171 -0.0337 1.0000 0.0182
-7.750 -0.6878 0.02622 0.01970 -0.0320 1.0000 0.0189
-7.500 -0.6717 0.02497 0.01831 -0.0304 1.0000 0.0196
-7.250 -0.6547 0.02378 0.01695 -0.0288 1.0000 0.0205
-7.000 -0.6367 0.02284 0.01582 -0.0273 1.0000 0.0219
-6.750 -0.6182 0.02181 0.01455 -0.0258 1.0000 0.0232
-6.500 -0.5992 0.02082 0.01335 -0.0242 1.0000 0.0240
-6.250 -0.5812 0.01943 0.01185 -0.0227 1.0000 0.0250
-6.000 -0.5611 0.01858 0.01096 -0.0216 0.9998 0.0262
-5.750 -0.5276 0.01791 0.01023 -0.0231 0.9964 0.0284
-5.500 -0.4945 0.01712 0.00930 -0.0245 0.9929 0.0302
-5.250 -0.4620 0.01638 0.00843 -0.0256 0.9887 0.0317
-5.000 -0.4289 0.01553 0.00755 -0.0270 0.9847 0.0338
-4.750 -0.3967 0.01500 0.00699 -0.0282 0.9800 0.0374
-4.500 -0.3641 0.01451 0.00641 -0.0293 0.9747 0.0415
-4.250 -0.3295 0.01391 0.00582 -0.0309 0.9708 0.0483
-4.000 -0.2996 0.01343 0.00535 -0.0314 0.9641 0.0595
-3.750 -0.2658 0.01299 0.00496 -0.0328 0.9591 0.0796
-3.500 -0.2337 0.01253 0.00462 -0.0339 0.9534 0.1095
-3.250 -0.2019 0.01210 0.00433 -0.0349 0.9469 0.1457
-3.000 -0.1667 0.01152 0.00406 -0.0367 0.9426 0.2140
-2.750 -0.1388 0.01098 0.00382 -0.0370 0.9335 0.2904
-2.500 -0.1055 0.01045 0.00359 -0.0383 0.9275 0.3725
-2.250 -0.0773 0.00997 0.00341 -0.0385 0.9177 0.4559
-2.000 -0.0488 0.00943 0.00327 -0.0385 0.9088 0.5621
-1.750 -0.0211 0.00894 0.00326 -0.0380 0.8999 0.6831
-1.500 0.0052 0.00878 0.00334 -0.0369 0.8886 0.7711
-1.250 0.0340 0.00874 0.00332 -0.0365 0.8771 0.8152
-1.000 0.0633 0.00871 0.00326 -0.0361 0.8647 0.8438
-0.750 0.0921 0.00869 0.00321 -0.0357 0.8512 0.8667
-0.500 0.1207 0.00870 0.00317 -0.0353 0.8366 0.8862
-0.250 0.1500 0.00872 0.00313 -0.0351 0.8210 0.9023
0.000 0.1801 0.00874 0.00309 -0.0350 0.8045 0.9165
0.250 0.2113 0.00879 0.00306 -0.0353 0.7874 0.9298
0.500 0.2431 0.00885 0.00303 -0.0357 0.7692 0.9420
0.750 0.2792 0.00891 0.00302 -0.0371 0.7496 0.9503
1.000 0.3134 0.00899 0.00300 -0.0382 0.7265 0.9592
1.250 0.3488 0.00909 0.00298 -0.0395 0.6999 0.9672
1.500 0.3846 0.00920 0.00297 -0.0411 0.6720 0.9735
1.750 0.4200 0.00932 0.00298 -0.0426 0.6463 0.9796
2.000 0.4536 0.00945 0.00299 -0.0438 0.6175 0.9852
2.250 0.4872 0.00960 0.00301 -0.0451 0.5876 0.9904
2.500 0.5198 0.00975 0.00307 -0.0462 0.5595 0.9957
2.750 0.5506 0.00992 0.00314 -0.0470 0.5331 1.0000
3.000 0.5698 0.01010 0.00324 -0.0453 0.5078 1.0000
3.250 0.5884 0.01031 0.00336 -0.0436 0.4793 1.0000
3.500 0.6066 0.01056 0.00349 -0.0417 0.4479 1.0000
3.750 0.6249 0.01084 0.00364 -0.0399 0.4166 1.0000
4.000 0.6439 0.01113 0.00381 -0.0383 0.3855 1.0000
4.250 0.6631 0.01145 0.00403 -0.0367 0.3535 1.0000
4.500 0.6827 0.01179 0.00426 -0.0352 0.3215 1.0000
4.750 0.7026 0.01218 0.00452 -0.0338 0.2886 1.0000
5.000 0.7228 0.01262 0.00482 -0.0325 0.2530 1.0000
5.250 0.7433 0.01309 0.00515 -0.0313 0.2188 1.0000
5.500 0.7641 0.01358 0.00553 -0.0302 0.1888 1.0000
5.750 0.7852 0.01409 0.00593 -0.0291 0.1654 1.0000
6.000 0.8065 0.01459 0.00637 -0.0281 0.1477 1.0000
6.250 0.8283 0.01508 0.00683 -0.0272 0.1323 1.0000
6.500 0.8503 0.01556 0.00731 -0.0263 0.1175 1.0000
6.750 0.8723 0.01604 0.00777 -0.0254 0.1039 1.0000
7.000 0.8940 0.01655 0.00827 -0.0246 0.0918 1.0000
7.250 0.9156 0.01707 0.00882 -0.0236 0.0826 1.0000
7.500 0.9365 0.01767 0.00943 -0.0226 0.0747 1.0000
7.750 0.9573 0.01828 0.01005 -0.0216 0.0671 1.0000
8.000 0.9777 0.01891 0.01077 -0.0206 0.0614 1.0000
8.250 0.9978 0.01957 0.01149 -0.0195 0.0561 1.0000
8.500 1.0165 0.02034 0.01231 -0.0182 0.0517 1.0000
8.750 1.0366 0.02097 0.01305 -0.0172 0.0469 1.0000
9.000 1.0541 0.02182 0.01387 -0.0159 0.0420 1.0000
9.250 1.0741 0.02241 0.01463 -0.0148 0.0379 1.0000
9.500 1.0919 0.02317 0.01544 -0.0136 0.0341 1.0000
9.750 1.1076 0.02410 0.01645 -0.0121 0.0312 1.0000
10.000 1.1246 0.02489 0.01737 -0.0107 0.0281 1.0000
10.250 1.1385 0.02584 0.01836 -0.0091 0.0251 1.0000
10.500 1.1510 0.02686 0.01952 -0.0072 0.0229 1.0000
10.750 1.1616 0.02790 0.02068 -0.0050 0.0210 1.0000
11.000 1.1698 0.02907 0.02196 -0.0028 0.0194 1.0000
11.250 1.1746 0.03054 0.02353 -0.0003 0.0182 1.0000
11.500 1.1823 0.03185 0.02502 0.0017 0.0168 1.0000
11.750 1.1876 0.03333 0.02665 0.0037 0.0157 1.0000
12.000 1.1924 0.03485 0.02827 0.0053 0.0146 1.0000
12.250 1.1920 0.03685 0.03036 0.0070 0.0139 1.0000
12.500 1.1926 0.03898 0.03267 0.0083 0.0134 1.0000
12.750 1.1911 0.04146 0.03535 0.0093 0.0130 1.0000
13.000 1.1885 0.04419 0.03828 0.0099 0.0126 1.0000
13.250 1.1841 0.04731 0.04158 0.0101 0.0122 1.0000
13.500 1.1784 0.05078 0.04523 0.0097 0.0120 1.0000
13.750 1.1715 0.05465 0.04928 0.0088 0.0117 1.0000
14.000 1.1628 0.05902 0.05384 0.0072 0.0115 1.0000
14.250 1.1525 0.06395 0.05894 0.0051 0.0113 1.0000
14.500 1.1407 0.06940 0.06457 0.0023 0.0112 1.0000
14.750 1.1267 0.07556 0.07091 -0.0010 0.0111 1.0000
15.000 1.1109 0.08241 0.07794 -0.0049 0.0111 1.0000
15.250 1.0922 0.09019 0.08591 -0.0094 0.0112 1.0000
15.500 1.0716 0.09890 0.09481 -0.0146 0.0111 1.0000
15.750 1.0468 0.10898 0.10508 -0.0206 0.0113 1.0000
16.000 1.0164 0.12113 0.11742 -0.0278 0.0115 1.0000
16.250 0.9692 0.13867 0.13516 -0.0378 0.0121 1.0000
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