RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 14 AIRFOIL (rg14-il) Reynolds number: 200,000 Max Cl/Cd: 64.54 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg14-il-200000.txt Download as CSV file: xf-rg14-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4036 0.10859 0.10513 -0.0187 1.0000 0.0440
-10.250 -0.4107 0.10465 0.10122 -0.0220 1.0000 0.0449
-10.000 -0.4167 0.10051 0.09714 -0.0249 1.0000 0.0452
-9.750 -0.4189 0.09625 0.09291 -0.0269 1.0000 0.0453
-9.500 -0.4232 0.09176 0.08845 -0.0293 1.0000 0.0454
-9.250 -0.4154 0.08606 0.08274 -0.0261 1.0000 0.0471
-9.000 -0.4100 0.08272 0.07941 -0.0255 1.0000 0.0483
-8.750 -0.4092 0.07897 0.07569 -0.0259 1.0000 0.0495
-8.500 -0.4114 0.07496 0.07171 -0.0269 1.0000 0.0507
-8.250 -0.4163 0.07068 0.06747 -0.0282 1.0000 0.0518
-8.000 -0.4244 0.06625 0.06308 -0.0300 1.0000 0.0528
-7.750 -0.4378 0.06166 0.05855 -0.0323 1.0000 0.0534
-7.500 -0.4567 0.05727 0.05419 -0.0341 1.0000 0.0535
-7.250 -0.4697 0.05239 0.04927 -0.0358 1.0000 0.0545
-7.000 -0.4916 0.04758 0.04408 -0.0378 1.0000 0.0575
-6.750 -0.4960 0.04466 0.04084 -0.0363 1.0000 0.0580
-6.500 -0.4958 0.03746 0.03381 -0.0357 1.0000 0.0597
-6.250 -0.5208 0.04679 0.04269 -0.0345 1.0000 0.0603
-6.000 -0.5101 0.04426 0.04014 -0.0331 1.0000 0.0621
-5.750 -0.4996 0.04150 0.03722 -0.0316 1.0000 0.0649
-5.500 -0.4878 0.03178 0.02605 -0.0275 1.0000 0.0336
-5.250 -0.4747 0.02696 0.02098 -0.0260 1.0000 0.0300
-5.000 -0.4570 0.02365 0.01717 -0.0241 1.0000 0.0281
-4.750 -0.4366 0.02112 0.01420 -0.0224 1.0000 0.0277
-4.500 -0.4149 0.01926 0.01203 -0.0209 1.0000 0.0277
-4.250 -0.3930 0.01786 0.01043 -0.0196 1.0000 0.0289
-4.000 -0.3711 0.01714 0.00955 -0.0183 1.0000 0.0322
-3.750 -0.3494 0.01561 0.00794 -0.0172 1.0000 0.0359
-3.500 -0.3277 0.01470 0.00699 -0.0160 1.0000 0.0407
-3.250 -0.3062 0.01371 0.00599 -0.0148 1.0000 0.0532
-3.000 -0.2848 0.01289 0.00534 -0.0139 1.0000 0.0932
-2.750 -0.2640 0.01224 0.00504 -0.0131 1.0000 0.1576
-2.500 -0.2325 0.01129 0.00485 -0.0149 0.9967 0.3232
-2.250 -0.1996 0.01016 0.00486 -0.0165 0.9909 0.5885
-2.000 -0.1705 0.00978 0.00526 -0.0156 0.9839 0.8163
-1.750 -0.1389 0.00983 0.00536 -0.0152 0.9760 0.8997
-1.500 -0.0877 0.00999 0.00544 -0.0190 0.9731 0.9549
-1.250 -0.0204 0.01012 0.00540 -0.0266 0.9739 0.9830
-1.000 0.0489 0.01015 0.00526 -0.0350 0.9756 1.0000
-0.750 0.0983 0.01009 0.00510 -0.0396 0.9697 1.0000
-0.500 0.1408 0.00994 0.00487 -0.0428 0.9598 1.0000
-0.250 0.1869 0.00978 0.00465 -0.0466 0.9518 1.0000
0.000 0.2349 0.00957 0.00440 -0.0507 0.9443 1.0000
0.250 0.2764 0.00934 0.00415 -0.0534 0.9327 1.0000
0.500 0.3166 0.00911 0.00389 -0.0557 0.9194 1.0000
0.750 0.3542 0.00889 0.00365 -0.0575 0.9034 1.0000
1.000 0.3854 0.00873 0.00347 -0.0578 0.8830 1.0000
1.250 0.4136 0.00862 0.00330 -0.0576 0.8612 1.0000
1.500 0.4373 0.00858 0.00321 -0.0564 0.8365 1.0000
1.750 0.4598 0.00859 0.00315 -0.0550 0.8110 1.0000
2.000 0.4815 0.00864 0.00312 -0.0535 0.7849 1.0000
2.250 0.5026 0.00872 0.00314 -0.0519 0.7581 1.0000
2.500 0.5233 0.00883 0.00316 -0.0502 0.7307 1.0000
2.750 0.5439 0.00898 0.00321 -0.0485 0.7023 1.0000
3.000 0.5645 0.00914 0.00329 -0.0469 0.6731 1.0000
3.250 0.5852 0.00934 0.00338 -0.0453 0.6431 1.0000
3.500 0.6058 0.00956 0.00353 -0.0437 0.6125 1.0000
3.750 0.6266 0.00980 0.00368 -0.0421 0.5801 1.0000
4.000 0.6476 0.01007 0.00385 -0.0406 0.5469 1.0000
4.250 0.6687 0.01037 0.00404 -0.0392 0.5122 1.0000
4.500 0.6899 0.01069 0.00426 -0.0379 0.4761 1.0000
4.750 0.7113 0.01104 0.00455 -0.0366 0.4385 1.0000
5.000 0.7326 0.01144 0.00484 -0.0354 0.3992 1.0000
5.250 0.7538 0.01188 0.00516 -0.0342 0.3580 1.0000
5.500 0.7748 0.01238 0.00552 -0.0330 0.3156 1.0000
5.750 0.7956 0.01294 0.00594 -0.0319 0.2716 1.0000
6.000 0.8158 0.01361 0.00642 -0.0307 0.2262 1.0000
6.250 0.8361 0.01433 0.00697 -0.0296 0.1819 1.0000
6.500 0.8559 0.01515 0.00765 -0.0285 0.1415 1.0000
6.750 0.8754 0.01606 0.00841 -0.0273 0.1084 1.0000
7.000 0.8937 0.01715 0.00937 -0.0259 0.0817 1.0000
7.250 0.9123 0.01823 0.01041 -0.0245 0.0590 1.0000
7.500 0.9272 0.01977 0.01186 -0.0226 0.0434 1.0000
7.750 0.9448 0.02105 0.01320 -0.0210 0.0337 1.0000
8.000 0.9620 0.02265 0.01495 -0.0192 0.0283 1.0000
8.250 0.9785 0.02413 0.01645 -0.0178 0.0233 1.0000
8.500 0.9944 0.02691 0.01947 -0.0160 0.0214 1.0000
8.750 1.0133 0.02888 0.02170 -0.0146 0.0203 1.0000
9.000 1.0304 0.03129 0.02442 -0.0131 0.0195 1.0000
9.250 1.0444 0.03413 0.02761 -0.0113 0.0191 1.0000
9.500 1.0543 0.03737 0.03125 -0.0092 0.0191 1.0000
9.750 1.0583 0.04096 0.03527 -0.0066 0.0192 1.0000
10.000 1.0563 0.04478 0.03950 -0.0039 0.0195 1.0000
10.250 1.0484 0.04864 0.04372 -0.0010 0.0199 1.0000
10.500 1.0341 0.05212 0.04747 0.0024 0.0202 1.0000
10.750 1.0168 0.05569 0.05128 0.0050 0.0205 1.0000
11.000 0.9968 0.05972 0.05552 0.0063 0.0206 1.0000
11.250 0.9769 0.06422 0.06021 0.0059 0.0209 1.0000
11.500 0.9562 0.06943 0.06559 0.0039 0.0210 1.0000
11.750 0.9353 0.07561 0.07193 0.0003 0.0212 1.0000
12.000 0.9142 0.08286 0.07931 -0.0047 0.0213 1.0000
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Polar data table (+)
Polar graphs
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