RG 14 9% AIRFOIL (rg149-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 9% AIRFOIL (rg149-il) Reynolds number: 50,000 Max Cl/Cd: 33.12 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg149-il-50000.txt Download as CSV file: xf-rg149-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RG 14 9% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4828 0.10901 0.10186 -0.0052 1.0000 0.2594
-9.000 -0.5025 0.10811 0.10109 -0.0066 1.0000 0.2699
-8.750 -0.4842 0.10339 0.09636 -0.0054 1.0000 0.2832
-8.500 -0.4763 0.09977 0.09277 -0.0047 1.0000 0.2968
-8.250 -0.4770 0.09695 0.09000 -0.0042 1.0000 0.3123
-8.000 -0.4813 0.09449 0.08763 -0.0035 1.0000 0.3279
-7.750 -0.4651 0.09024 0.08338 -0.0020 1.0000 0.3461
-7.500 -0.4575 0.08693 0.08011 -0.0008 1.0000 0.3624
-7.250 -0.4524 0.08380 0.07703 0.0004 1.0000 0.3790
-7.000 -0.4498 0.08089 0.07419 0.0018 1.0000 0.3961
-6.750 -0.4628 0.07899 0.07243 0.0042 1.0000 0.4175
-6.500 -0.4462 0.07513 0.06856 0.0056 1.0000 0.4353
-6.250 -0.5371 0.05428 0.04692 -0.0310 1.0000 0.1521
-6.000 -0.5290 0.04900 0.04122 -0.0310 1.0000 0.1421
-5.750 -0.5157 0.04484 0.03664 -0.0302 1.0000 0.1363
-5.500 -0.5009 0.04089 0.03226 -0.0292 1.0000 0.1322
-5.250 -0.4840 0.03725 0.02803 -0.0281 1.0000 0.1297
-5.000 -0.4650 0.03458 0.02495 -0.0268 1.0000 0.1329
-4.750 -0.4444 0.03217 0.02198 -0.0255 1.0000 0.1382
-4.500 -0.4224 0.02972 0.01924 -0.0243 1.0000 0.1428
-4.250 -0.3991 0.02772 0.01699 -0.0231 1.0000 0.1505
-4.000 -0.3763 0.02603 0.01514 -0.0218 1.0000 0.1663
-3.750 -0.3525 0.02426 0.01340 -0.0205 1.0000 0.1867
-3.500 -0.3294 0.02266 0.01193 -0.0191 1.0000 0.2282
-3.250 -0.3075 0.02083 0.01063 -0.0177 1.0000 0.3114
-3.000 -0.2966 0.01814 0.00965 -0.0138 1.0000 0.5234
-2.750 -0.1107 0.01822 0.00961 -0.0330 1.0000 1.0000
-2.500 -0.1074 0.01789 0.00910 -0.0300 1.0000 1.0000
-2.250 -0.1035 0.01766 0.00872 -0.0269 1.0000 1.0000
-2.000 -0.0993 0.01750 0.00838 -0.0236 1.0000 1.0000
-1.750 -0.0945 0.01740 0.00814 -0.0204 1.0000 1.0000
-1.500 -0.0886 0.01736 0.00794 -0.0173 1.0000 1.0000
-1.250 -0.0814 0.01737 0.00779 -0.0145 1.0000 1.0000
-1.000 -0.0722 0.01743 0.00771 -0.0120 1.0000 1.0000
-0.750 -0.0610 0.01755 0.00768 -0.0099 1.0000 1.0000
-0.500 -0.0482 0.01773 0.00770 -0.0082 1.0000 1.0000
-0.250 -0.0342 0.01795 0.00780 -0.0067 1.0000 1.0000
0.000 -0.0194 0.01823 0.00797 -0.0054 1.0000 1.0000
0.250 -0.0042 0.01857 0.00820 -0.0044 1.0000 1.0000
0.500 0.0112 0.01895 0.00849 -0.0034 1.0000 1.0000
0.750 0.0268 0.01940 0.00887 -0.0026 1.0000 1.0000
1.000 0.0423 0.01991 0.00932 -0.0020 1.0000 1.0000
1.250 0.0577 0.02048 0.00984 -0.0015 1.0000 1.0000
1.500 0.0731 0.02112 0.01045 -0.0011 1.0000 1.0000
1.750 0.0956 0.02195 0.01126 -0.0022 0.9967 1.0000
2.000 0.1572 0.02334 0.01269 -0.0104 0.9748 1.0000
2.250 0.2148 0.02446 0.01389 -0.0175 0.9523 1.0000
2.500 0.2730 0.02538 0.01492 -0.0241 0.9298 1.0000
2.750 0.3224 0.02604 0.01571 -0.0289 0.9055 1.0000
3.000 0.3771 0.02654 0.01639 -0.0339 0.8815 1.0000
3.250 0.4361 0.02672 0.01680 -0.0391 0.8572 1.0000
3.500 0.4928 0.02655 0.01691 -0.0431 0.8300 1.0000
3.750 0.5575 0.02551 0.01617 -0.0465 0.7992 1.0000
4.000 0.6054 0.02462 0.01553 -0.0469 0.7672 1.0000
4.250 0.6403 0.02418 0.01526 -0.0457 0.7347 1.0000
4.500 0.6745 0.02365 0.01486 -0.0440 0.6997 1.0000
4.750 0.7027 0.02327 0.01455 -0.0414 0.6596 1.0000
5.000 0.7282 0.02298 0.01427 -0.0383 0.6135 1.0000
5.250 0.7499 0.02293 0.01409 -0.0348 0.5601 1.0000
5.500 0.7687 0.02321 0.01413 -0.0313 0.4996 1.0000
5.750 0.7864 0.02387 0.01443 -0.0280 0.4366 1.0000
6.000 0.8036 0.02489 0.01515 -0.0252 0.3787 1.0000
6.250 0.8215 0.02615 0.01614 -0.0230 0.3294 1.0000
6.500 0.8419 0.02764 0.01735 -0.0212 0.2893 1.0000
6.750 0.8611 0.02923 0.01891 -0.0195 0.2554 1.0000
7.000 0.8828 0.03109 0.02071 -0.0182 0.2290 1.0000
7.250 0.9043 0.03297 0.02255 -0.0171 0.2058 1.0000
7.500 0.9244 0.03529 0.02505 -0.0157 0.1881 1.0000
7.750 0.9426 0.03769 0.02769 -0.0142 0.1724 1.0000
8.000 0.9619 0.04058 0.03074 -0.0130 0.1608 1.0000
8.250 0.9799 0.04336 0.03359 -0.0118 0.1483 1.0000
8.500 0.9848 0.04707 0.03811 -0.0092 0.1435 1.0000
8.750 1.0042 0.05044 0.04137 -0.0084 0.1344 1.0000
9.000 0.9984 0.05437 0.04608 -0.0055 0.1312 1.0000
9.250 0.9923 0.05884 0.05110 -0.0033 0.1293 1.0000
9.500 0.9812 0.06378 0.05644 -0.0015 0.1293 1.0000
9.750 0.9651 0.06887 0.06179 -0.0001 0.1301 1.0000
10.000 0.9464 0.07404 0.06714 0.0007 0.1315 1.0000
10.250 0.9272 0.07911 0.07230 0.0012 0.1328 1.0000
10.500 0.9125 0.08464 0.07788 0.0008 0.1339 1.0000
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Polar data table (+)
Polar graphs
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