RG 14 10% AIRFOIL (rg1410-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 10% AIRFOIL (rg1410-il) Reynolds number: 100,000 Max Cl/Cd: 46.44 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg1410-il-100000-n5.txt Download as CSV file: xf-rg1410-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5395 0.08913 0.08391 -0.0307 1.0000 0.0325
-10.000 -0.5504 0.08258 0.07743 -0.0343 1.0000 0.0322
-9.750 -0.5669 0.07431 0.06922 -0.0398 1.0000 0.0317
-9.500 -0.5965 0.06482 0.05971 -0.0469 1.0000 0.0310
-9.250 -0.6262 0.05963 0.05444 -0.0471 1.0000 0.0307
-9.000 -0.6480 0.05478 0.04939 -0.0461 1.0000 0.0305
-8.750 -0.6636 0.05022 0.04455 -0.0443 1.0000 0.0305
-8.500 -0.6721 0.04609 0.04009 -0.0422 1.0000 0.0307
-8.250 -0.6748 0.04234 0.03595 -0.0399 1.0000 0.0311
-8.000 -0.6727 0.03891 0.03209 -0.0375 1.0000 0.0317
-7.750 -0.6660 0.03604 0.02877 -0.0353 1.0000 0.0329
-7.500 -0.6562 0.03356 0.02572 -0.0330 1.0000 0.0345
-7.250 -0.6435 0.03126 0.02318 -0.0312 1.0000 0.0357
-7.000 -0.6280 0.02952 0.02126 -0.0296 1.0000 0.0367
-6.750 -0.6113 0.02797 0.01951 -0.0280 1.0000 0.0379
-6.500 -0.5936 0.02655 0.01786 -0.0264 1.0000 0.0395
-6.250 -0.5752 0.02538 0.01647 -0.0249 1.0000 0.0421
-6.000 -0.5558 0.02424 0.01506 -0.0234 1.0000 0.0443
-5.750 -0.5372 0.02290 0.01367 -0.0219 1.0000 0.0460
-5.500 -0.5184 0.02192 0.01267 -0.0205 1.0000 0.0482
-5.250 -0.4993 0.02106 0.01173 -0.0190 1.0000 0.0510
-5.000 -0.4797 0.02033 0.01085 -0.0176 1.0000 0.0552
-4.750 -0.4610 0.01958 0.01013 -0.0163 1.0000 0.0603
-4.500 -0.4415 0.01895 0.00943 -0.0149 1.0000 0.0670
-4.250 -0.4206 0.01827 0.00878 -0.0139 0.9995 0.0755
-4.000 -0.3849 0.01767 0.00816 -0.0159 0.9940 0.0949
-3.750 -0.3507 0.01706 0.00769 -0.0177 0.9877 0.1238
-3.500 -0.3158 0.01648 0.00734 -0.0196 0.9818 0.1682
-3.250 -0.2832 0.01588 0.00702 -0.0211 0.9746 0.2279
-3.000 -0.2497 0.01529 0.00675 -0.0227 0.9681 0.3057
-2.750 -0.2184 0.01469 0.00653 -0.0237 0.9603 0.4009
-2.500 -0.1881 0.01407 0.00640 -0.0243 0.9528 0.5183
-2.250 -0.1584 0.01356 0.00647 -0.0239 0.9454 0.6577
-2.000 -0.1289 0.01348 0.00668 -0.0230 0.9374 0.7708
-1.750 -0.0945 0.01350 0.00670 -0.0234 0.9302 0.8325
-1.500 -0.0604 0.01354 0.00668 -0.0237 0.9218 0.8724
-1.250 -0.0176 0.01357 0.00664 -0.0259 0.9156 0.9034
-1.000 0.0255 0.01360 0.00657 -0.0283 0.9078 0.9284
-0.750 0.0772 0.01359 0.00647 -0.0326 0.9013 0.9461
-0.500 0.1299 0.01356 0.00634 -0.0373 0.8933 0.9606
-0.250 0.1846 0.01345 0.00615 -0.0425 0.8848 0.9720
0.000 0.2346 0.01331 0.00596 -0.0468 0.8725 0.9820
0.250 0.2846 0.01313 0.00572 -0.0512 0.8590 0.9904
0.500 0.3323 0.01295 0.00550 -0.0552 0.8436 0.9987
0.750 0.3638 0.01284 0.00533 -0.0558 0.8255 1.0000
1.000 0.3888 0.01278 0.00522 -0.0552 0.8053 1.0000
1.250 0.4134 0.01274 0.00513 -0.0544 0.7847 1.0000
1.500 0.4379 0.01272 0.00506 -0.0536 0.7642 1.0000
1.750 0.4601 0.01275 0.00504 -0.0523 0.7412 1.0000
2.000 0.4823 0.01279 0.00500 -0.0510 0.7172 1.0000
2.250 0.5038 0.01286 0.00500 -0.0495 0.6917 1.0000
2.500 0.5243 0.01297 0.00503 -0.0478 0.6647 1.0000
2.750 0.5445 0.01310 0.00507 -0.0461 0.6369 1.0000
3.000 0.5645 0.01327 0.00515 -0.0444 0.6097 1.0000
3.250 0.5847 0.01346 0.00527 -0.0428 0.5845 1.0000
3.500 0.6049 0.01367 0.00542 -0.0412 0.5603 1.0000
3.750 0.6251 0.01390 0.00560 -0.0396 0.5357 1.0000
4.000 0.6449 0.01416 0.00579 -0.0380 0.5094 1.0000
4.250 0.6644 0.01445 0.00601 -0.0363 0.4807 1.0000
4.500 0.6837 0.01478 0.00624 -0.0346 0.4492 1.0000
4.750 0.7030 0.01514 0.00650 -0.0329 0.4162 1.0000
5.000 0.7222 0.01555 0.00679 -0.0313 0.3824 1.0000
5.250 0.7415 0.01600 0.00715 -0.0298 0.3475 1.0000
5.500 0.7608 0.01649 0.00753 -0.0283 0.3124 1.0000
5.750 0.7796 0.01706 0.00796 -0.0268 0.2770 1.0000
6.000 0.7987 0.01766 0.00845 -0.0254 0.2435 1.0000
6.250 0.8177 0.01831 0.00901 -0.0241 0.2140 1.0000
6.500 0.8365 0.01901 0.00960 -0.0227 0.1902 1.0000
6.750 0.8557 0.01971 0.01026 -0.0214 0.1700 1.0000
7.000 0.8743 0.02048 0.01097 -0.0201 0.1533 1.0000
7.250 0.8929 0.02126 0.01175 -0.0188 0.1391 1.0000
7.500 0.9116 0.02204 0.01258 -0.0175 0.1262 1.0000
7.750 0.9301 0.02284 0.01341 -0.0162 0.1150 1.0000
8.000 0.9480 0.02367 0.01424 -0.0149 0.1053 1.0000
8.250 0.9665 0.02446 0.01512 -0.0137 0.0960 1.0000
8.500 0.9839 0.02539 0.01610 -0.0123 0.0885 1.0000
8.750 1.0002 0.02634 0.01710 -0.0108 0.0817 1.0000
9.000 1.0169 0.02738 0.01826 -0.0094 0.0755 1.0000
9.250 1.0326 0.02845 0.01941 -0.0079 0.0705 1.0000
9.500 1.0473 0.02971 0.02073 -0.0064 0.0659 1.0000
9.750 1.0626 0.03084 0.02204 -0.0049 0.0609 1.0000
10.000 1.0753 0.03212 0.02334 -0.0033 0.0572 1.0000
10.250 1.0886 0.03359 0.02500 -0.0017 0.0537 1.0000
10.500 1.0990 0.03483 0.02646 0.0003 0.0496 1.0000
10.750 1.1066 0.03608 0.02776 0.0023 0.0467 1.0000
11.000 1.1138 0.03778 0.02962 0.0043 0.0438 1.0000
11.250 1.1200 0.03941 0.03151 0.0062 0.0407 1.0000
11.500 1.1240 0.04098 0.03321 0.0081 0.0382 1.0000
11.750 1.1255 0.04274 0.03500 0.0097 0.0362 1.0000
12.000 1.1260 0.04514 0.03766 0.0112 0.0344 1.0000
12.250 1.1243 0.04771 0.04052 0.0124 0.0326 1.0000
12.500 1.1210 0.05053 0.04357 0.0133 0.0313 1.0000
12.750 1.1164 0.05353 0.04675 0.0137 0.0302 1.0000
13.000 1.1110 0.05670 0.05010 0.0136 0.0293 1.0000
13.250 1.1050 0.06008 0.05358 0.0131 0.0285 1.0000
13.500 1.0976 0.06389 0.05749 0.0121 0.0278 1.0000
13.750 1.0826 0.06917 0.06301 0.0101 0.0273 1.0000
14.000 1.0661 0.07509 0.06918 0.0073 0.0271 1.0000
14.250 1.0461 0.08203 0.07636 0.0035 0.0269 1.0000
14.500 1.0245 0.08981 0.08434 -0.0012 0.0270 1.0000
14.750 1.0019 0.09839 0.09310 -0.0065 0.0272 1.0000
15.000 0.9771 0.10812 0.10295 -0.0126 0.0275 1.0000
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