RG 14 AIRFOIL (rg14-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RG 14 AIRFOIL (rg14-il) Reynolds number: 200,000 Max Cl/Cd: 59.31 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rg14-il-200000-n5.txt Download as CSV file: xf-rg14-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5093 0.08757 0.08400 -0.0230 1.0000 0.0138
-9.000 -0.5132 0.08298 0.07946 -0.0252 1.0000 0.0136
-8.750 -0.5190 0.07814 0.07468 -0.0277 1.0000 0.0134
-8.500 -0.5275 0.07312 0.06972 -0.0309 1.0000 0.0132
-8.250 -0.5416 0.06793 0.06456 -0.0344 1.0000 0.0130
-8.000 -0.5514 0.06221 0.05880 -0.0371 1.0000 0.0128
-7.750 -0.5593 0.05656 0.05305 -0.0383 1.0000 0.0126
-7.500 -0.5650 0.05097 0.04728 -0.0385 1.0000 0.0123
-7.250 -0.5688 0.04533 0.04138 -0.0376 1.0000 0.0120
-7.000 -0.5697 0.03987 0.03556 -0.0360 1.0000 0.0117
-6.750 -0.5668 0.03485 0.03008 -0.0340 1.0000 0.0115
-6.500 -0.5593 0.03054 0.02525 -0.0318 1.0000 0.0113
-6.250 -0.5473 0.02708 0.02127 -0.0297 1.0000 0.0113
-6.000 -0.5316 0.02446 0.01820 -0.0279 1.0000 0.0113
-5.750 -0.5138 0.02233 0.01569 -0.0263 1.0000 0.0115
-5.500 -0.4946 0.02062 0.01369 -0.0248 1.0000 0.0119
-5.250 -0.4745 0.01917 0.01196 -0.0233 1.0000 0.0123
-5.000 -0.4516 0.01791 0.01050 -0.0225 0.9994 0.0128
-4.750 -0.4182 0.01670 0.00909 -0.0238 0.9960 0.0140
-4.500 -0.3850 0.01575 0.00801 -0.0251 0.9923 0.0152
-4.250 -0.3523 0.01497 0.00719 -0.0265 0.9878 0.0186
-4.000 -0.3176 0.01422 0.00631 -0.0280 0.9837 0.0216
-3.750 -0.2855 0.01343 0.00543 -0.0289 0.9784 0.0296
-3.500 -0.2521 0.01286 0.00487 -0.0302 0.9729 0.0480
-3.250 -0.2181 0.01229 0.00453 -0.0319 0.9682 0.0888
-3.000 -0.1873 0.01178 0.00419 -0.0328 0.9611 0.1350
-2.750 -0.1522 0.01123 0.00389 -0.0346 0.9563 0.2030
-2.500 -0.1227 0.01071 0.00363 -0.0352 0.9480 0.2793
-2.250 -0.0887 0.01005 0.00337 -0.0369 0.9426 0.3976
-2.000 -0.0619 0.00934 0.00320 -0.0368 0.9328 0.5381
-1.750 -0.0358 0.00873 0.00320 -0.0360 0.9240 0.6924
-1.500 -0.0064 0.00854 0.00323 -0.0355 0.9157 0.7936
-1.250 0.0222 0.00847 0.00317 -0.0350 0.9045 0.8402
-1.000 0.0522 0.00842 0.00310 -0.0348 0.8932 0.8717
-0.750 0.0838 0.00839 0.00303 -0.0350 0.8810 0.8956
-0.500 0.1167 0.00836 0.00295 -0.0355 0.8674 0.9161
-0.250 0.1523 0.00835 0.00286 -0.0367 0.8522 0.9319
0.000 0.1891 0.00835 0.00278 -0.0382 0.8355 0.9453
0.250 0.2268 0.00837 0.00271 -0.0399 0.8172 0.9576
0.500 0.2646 0.00841 0.00265 -0.0417 0.7966 0.9679
0.750 0.3047 0.00845 0.00258 -0.0441 0.7743 0.9756
1.000 0.3421 0.00851 0.00253 -0.0460 0.7502 0.9834
1.250 0.3799 0.00857 0.00249 -0.0481 0.7241 0.9897
1.500 0.4145 0.00865 0.00246 -0.0495 0.6972 0.9960
1.750 0.4445 0.00875 0.00246 -0.0500 0.6693 1.0000
2.000 0.4649 0.00889 0.00248 -0.0485 0.6425 1.0000
2.250 0.4853 0.00904 0.00255 -0.0470 0.6154 1.0000
2.500 0.5056 0.00921 0.00262 -0.0455 0.5879 1.0000
2.750 0.5261 0.00940 0.00271 -0.0440 0.5596 1.0000
3.000 0.5467 0.00962 0.00282 -0.0426 0.5309 1.0000
3.500 0.5884 0.01011 0.00314 -0.0399 0.4711 1.0000
3.750 0.6098 0.01039 0.00332 -0.0386 0.4397 1.0000
4.000 0.6315 0.01070 0.00353 -0.0375 0.4080 1.0000
4.250 0.6533 0.01104 0.00376 -0.0364 0.3752 1.0000
4.500 0.6755 0.01139 0.00401 -0.0354 0.3418 1.0000
4.750 0.6977 0.01179 0.00430 -0.0345 0.3082 1.0000
5.000 0.7201 0.01220 0.00466 -0.0336 0.2741 1.0000
5.500 0.7646 0.01315 0.00540 -0.0319 0.2071 1.0000
5.750 0.7868 0.01367 0.00583 -0.0311 0.1760 1.0000
6.000 0.8086 0.01426 0.00631 -0.0302 0.1453 1.0000
6.250 0.8305 0.01487 0.00682 -0.0294 0.1178 1.0000
6.500 0.8520 0.01553 0.00743 -0.0285 0.0920 1.0000
6.750 0.8738 0.01617 0.00804 -0.0277 0.0720 1.0000
7.000 0.8951 0.01687 0.00872 -0.0268 0.0567 1.0000
7.250 0.9158 0.01765 0.00948 -0.0258 0.0419 1.0000
7.500 0.9362 0.01848 0.01030 -0.0248 0.0305 1.0000
7.750 0.9552 0.01946 0.01129 -0.0236 0.0218 1.0000
8.000 0.9749 0.02036 0.01234 -0.0224 0.0178 1.0000
8.250 0.9913 0.02163 0.01372 -0.0208 0.0142 1.0000
8.500 1.0104 0.02253 0.01477 -0.0197 0.0120 1.0000
8.750 1.0277 0.02359 0.01593 -0.0184 0.0105 1.0000
9.000 1.0397 0.02525 0.01772 -0.0164 0.0095 1.0000
9.250 1.0541 0.02665 0.01931 -0.0147 0.0090 1.0000
9.500 1.0673 0.02819 0.02105 -0.0128 0.0087 1.0000
9.750 1.0789 0.02995 0.02302 -0.0109 0.0082 1.0000
10.000 1.0893 0.03182 0.02511 -0.0089 0.0080 1.0000
10.250 1.0973 0.03386 0.02740 -0.0068 0.0077 1.0000
10.500 1.1015 0.03597 0.02975 -0.0042 0.0075 1.0000
10.750 1.1025 0.03825 0.03229 -0.0015 0.0074 1.0000
11.000 1.1001 0.04078 0.03507 0.0010 0.0072 1.0000
11.250 1.0949 0.04353 0.03809 0.0032 0.0072 1.0000
11.500 1.0868 0.04658 0.04145 0.0049 0.0071 1.0000
11.750 1.0760 0.05015 0.04527 0.0057 0.0071 1.0000
12.000 1.0633 0.05422 0.04958 0.0055 0.0071 1.0000
12.250 1.0485 0.05902 0.05462 0.0041 0.0071 1.0000
12.500 1.0317 0.06470 0.06052 0.0014 0.0071 1.0000
12.750 1.0136 0.07133 0.06736 -0.0025 0.0071 1.0000
13.000 0.9938 0.07912 0.07535 -0.0077 0.0072 1.0000
13.250 0.9721 0.08821 0.08457 -0.0139 0.0073 1.0000
13.500 0.9498 0.09834 0.09485 -0.0206 0.0075 1.0000
13.750 0.9231 0.11058 0.10721 -0.0282 0.0076 1.0000
14.000 0.8893 0.12588 0.12257 -0.0365 0.0080 1.0000
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Polar data table (+)
Polar graphs
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