RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14A-1.4/7.0 AIRFOIL (rg14a147-il) Reynolds number: 200,000 Max Cl/Cd: 62.85 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg14a147-il-200000.txt Download as CSV file: xf-rg14a147-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5161 0.08689 0.08342 -0.0147 1.0000 0.0357
-8.000 -0.5176 0.08319 0.07977 -0.0166 1.0000 0.0366
-7.750 -0.5221 0.07944 0.07608 -0.0188 1.0000 0.0373
-7.500 -0.5246 0.07509 0.07176 -0.0225 1.0000 0.0381
-7.250 -0.5233 0.07049 0.06713 -0.0262 1.0000 0.0393
-7.000 -0.5189 0.06535 0.06186 -0.0310 1.0000 0.0414
-6.750 -0.5121 0.06195 0.05811 -0.0335 1.0000 0.0426
-6.500 -0.5094 0.05703 0.05296 -0.0339 1.0000 0.0431
-6.250 -0.5041 0.05137 0.04744 -0.0335 1.0000 0.0447
-6.000 -0.4930 0.04851 0.04458 -0.0327 1.0000 0.0463
-5.750 -0.4806 0.04550 0.04145 -0.0321 1.0000 0.0489
-5.250 -0.4536 0.03816 0.03346 -0.0309 1.0000 0.0582
-5.000 -0.4375 0.03564 0.03088 -0.0298 1.0000 0.0614
-4.750 -0.4208 0.03290 0.02762 -0.0287 1.0000 0.0708
-4.500 -0.3922 0.02566 0.01945 -0.0251 1.0000 0.0294
-4.250 -0.3720 0.02208 0.01542 -0.0237 1.0000 0.0271
-4.000 -0.3489 0.02075 0.01372 -0.0223 1.0000 0.0296
-3.750 -0.3256 0.01929 0.01193 -0.0209 1.0000 0.0303
-3.500 -0.3020 0.01710 0.00949 -0.0197 1.0000 0.0301
-3.000 -0.2560 0.01372 0.00595 -0.0172 1.0000 0.0336
-2.750 -0.2334 0.01305 0.00526 -0.0162 1.0000 0.0407
-2.500 -0.2103 0.01216 0.00435 -0.0152 1.0000 0.0550
-2.250 -0.1891 0.01004 0.00358 -0.0149 1.0000 0.3378
-2.000 -0.1763 0.00860 0.00363 -0.0120 1.0000 0.6877
-1.750 -0.1681 0.00835 0.00395 -0.0064 1.0000 0.9006
-1.500 -0.0881 0.00837 0.00377 -0.0162 1.0000 1.0000
-1.250 -0.0765 0.00840 0.00365 -0.0137 1.0000 1.0000
-1.000 -0.0611 0.00849 0.00363 -0.0119 1.0000 1.0000
-0.750 -0.0241 0.00865 0.00366 -0.0144 0.9956 1.0000
-0.500 0.0225 0.00878 0.00367 -0.0186 0.9880 1.0000
-0.250 0.0703 0.00889 0.00368 -0.0230 0.9810 1.0000
0.000 0.1155 0.00890 0.00363 -0.0267 0.9719 1.0000
0.250 0.1605 0.00886 0.00357 -0.0303 0.9624 1.0000
0.500 0.2113 0.00878 0.00348 -0.0350 0.9557 1.0000
0.750 0.2554 0.00863 0.00334 -0.0382 0.9445 1.0000
1.000 0.2978 0.00846 0.00318 -0.0410 0.9317 1.0000
1.250 0.3388 0.00828 0.00303 -0.0434 0.9163 1.0000
1.500 0.3731 0.00815 0.00293 -0.0443 0.8947 1.0000
1.750 0.4044 0.00806 0.00284 -0.0445 0.8702 1.0000
2.000 0.4312 0.00805 0.00279 -0.0437 0.8419 1.0000
2.250 0.4556 0.00811 0.00278 -0.0425 0.8106 1.0000
2.500 0.4790 0.00821 0.00280 -0.0411 0.7772 1.0000
2.750 0.5019 0.00839 0.00291 -0.0397 0.7424 1.0000
3.000 0.5242 0.00858 0.00303 -0.0382 0.7047 1.0000
3.250 0.5464 0.00879 0.00314 -0.0368 0.6626 1.0000
3.500 0.5683 0.00907 0.00327 -0.0353 0.6181 1.0000
3.750 0.5902 0.00939 0.00345 -0.0339 0.5689 1.0000
4.000 0.6119 0.00977 0.00371 -0.0325 0.5163 1.0000
4.250 0.6331 0.01022 0.00396 -0.0312 0.4563 1.0000
4.500 0.6527 0.01085 0.00423 -0.0297 0.3726 1.0000
4.750 0.6725 0.01160 0.00460 -0.0284 0.2844 1.0000
5.000 0.6932 0.01239 0.00508 -0.0274 0.2090 1.0000
5.250 0.7116 0.01365 0.00582 -0.0262 0.1082 1.0000
5.500 0.7289 0.01534 0.00718 -0.0244 0.0535 1.0000
5.750 0.7496 0.01648 0.00838 -0.0231 0.0438 1.0000
6.000 0.7675 0.01834 0.01023 -0.0214 0.0385 1.0000
6.250 0.7909 0.01929 0.01134 -0.0204 0.0342 1.0000
6.500 0.8130 0.02064 0.01276 -0.0193 0.0303 1.0000
6.750 0.8341 0.02372 0.01597 -0.0181 0.0279 1.0000
7.000 0.8566 0.02567 0.01827 -0.0169 0.0257 1.0000
7.250 0.8782 0.02763 0.02058 -0.0156 0.0233 1.0000
7.500 0.8966 0.03088 0.02429 -0.0139 0.0229 1.0000
7.750 0.9105 0.03497 0.02899 -0.0118 0.0235 1.0000
8.000 0.9191 0.03975 0.03430 -0.0095 0.0248 1.0000
8.250 0.9202 0.04577 0.04073 -0.0076 0.0266 1.0000
11.500 0.6900 0.12285 0.11981 -0.0253 0.0506 1.0000
11.750 0.6834 0.12861 0.12555 -0.0288 0.0505 1.0000
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Polar data table (+)
Polar graphs
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