RG 8 AIRFOIL (rg8-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RG 8 AIRFOIL (rg8-il) Reynolds number: 50,000 Max Cl/Cd: 35.51 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rg8-il-50000.txt Download as CSV file: xf-rg8-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RG 8 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4106 0.10765 0.10052 -0.0181 1.0000 0.2840
-8.750 -0.4213 0.10571 0.09869 -0.0180 1.0000 0.2945
-8.500 -0.4215 0.10329 0.09633 -0.0171 1.0000 0.3071
-8.250 -0.4045 0.09879 0.09183 -0.0162 1.0000 0.3149
-8.000 -0.4122 0.09642 0.08957 -0.0154 1.0000 0.3252
-7.500 -0.4085 0.09029 0.08354 -0.0135 1.0000 0.3417
-7.250 -0.5174 0.07680 0.07047 -0.0350 1.0000 0.1889
-7.000 -0.5539 0.06248 0.05569 -0.0464 1.0000 0.1326
-6.750 -0.5465 0.05820 0.05130 -0.0460 1.0000 0.1293
-6.500 -0.5407 0.05366 0.04653 -0.0463 1.0000 0.1271
-6.250 -0.5323 0.04893 0.04143 -0.0470 1.0000 0.1246
-6.000 -0.5194 0.04415 0.03606 -0.0477 1.0000 0.1220
-5.750 -0.5014 0.03997 0.03121 -0.0481 1.0000 0.1206
-5.500 -0.4807 0.03677 0.02758 -0.0478 1.0000 0.1219
-5.250 -0.4586 0.03414 0.02455 -0.0474 1.0000 0.1268
-5.000 -0.4356 0.03174 0.02179 -0.0469 1.0000 0.1356
-4.750 -0.4111 0.02960 0.01926 -0.0462 1.0000 0.1469
-4.500 -0.3885 0.02773 0.01749 -0.0452 1.0000 0.1666
-4.250 -0.3653 0.02599 0.01573 -0.0443 1.0000 0.2031
-4.000 -0.3434 0.02430 0.01442 -0.0434 1.0000 0.2599
-3.750 -0.3220 0.02257 0.01323 -0.0422 1.0000 0.3409
-3.500 -0.3043 0.02142 0.01304 -0.0395 1.0000 0.4639
-3.250 -0.2946 0.02160 0.01377 -0.0339 1.0000 0.5899
-3.000 -0.2898 0.02199 0.01432 -0.0271 1.0000 0.6677
-2.750 -0.2864 0.02220 0.01457 -0.0203 1.0000 0.7263
-2.500 -0.2847 0.02223 0.01459 -0.0133 1.0000 0.7752
-2.250 -0.2832 0.02207 0.01440 -0.0067 1.0000 0.8213
-2.000 -0.2800 0.02178 0.01406 -0.0007 1.0000 0.8672
-1.750 -0.2599 0.02153 0.01370 0.0022 1.0000 0.9214
-1.500 -0.0954 0.02226 0.01357 -0.0218 1.0000 0.9987
-1.250 -0.1044 0.02175 0.01303 -0.0186 1.0000 1.0000
-1.000 -0.1156 0.02120 0.01246 -0.0150 1.0000 1.0000
-0.750 -0.1123 0.02089 0.01205 -0.0137 1.0000 1.0000
-0.500 -0.0948 0.02090 0.01189 -0.0146 1.0000 1.0000
-0.250 -0.0721 0.02112 0.01192 -0.0162 1.0000 1.0000
0.000 -0.0481 0.02147 0.01208 -0.0178 1.0000 1.0000
0.250 -0.0243 0.02193 0.01237 -0.0193 1.0000 1.0000
0.500 -0.0012 0.02247 0.01276 -0.0206 1.0000 1.0000
0.750 0.0209 0.02309 0.01325 -0.0216 1.0000 1.0000
1.000 0.0420 0.02378 0.01382 -0.0226 1.0000 1.0000
1.250 0.0622 0.02454 0.01448 -0.0234 1.0000 1.0000
1.500 0.1156 0.02609 0.01594 -0.0302 0.9846 1.0000
1.750 0.1668 0.02733 0.01711 -0.0363 0.9654 1.0000
2.000 0.2191 0.02847 0.01822 -0.0423 0.9469 1.0000
2.250 0.2657 0.02937 0.01912 -0.0469 0.9274 1.0000
2.500 0.3117 0.03015 0.01992 -0.0512 0.9077 1.0000
2.750 0.3640 0.03083 0.02064 -0.0561 0.8889 1.0000
3.000 0.4016 0.03138 0.02126 -0.0585 0.8676 1.0000
3.250 0.4492 0.03175 0.02172 -0.0620 0.8476 1.0000
3.500 0.4953 0.03197 0.02206 -0.0649 0.8275 1.0000
3.750 0.5360 0.03213 0.02237 -0.0668 0.8059 1.0000
4.000 0.5927 0.03164 0.02207 -0.0702 0.7871 1.0000
4.250 0.6320 0.03151 0.02213 -0.0712 0.7646 1.0000
4.500 0.6908 0.03048 0.02133 -0.0739 0.7442 1.0000
4.750 0.7326 0.02997 0.02100 -0.0744 0.7204 1.0000
5.000 0.7914 0.02853 0.01980 -0.0762 0.6973 1.0000
5.250 0.8304 0.02796 0.01938 -0.0758 0.6693 1.0000
5.500 0.8684 0.02747 0.01902 -0.0752 0.6393 1.0000
5.750 0.8990 0.02738 0.01899 -0.0739 0.6070 1.0000
6.000 0.9263 0.02748 0.01914 -0.0722 0.5726 1.0000
6.250 0.9563 0.02750 0.01911 -0.0707 0.5371 1.0000
6.500 0.9788 0.02794 0.01956 -0.0685 0.5001 1.0000
6.750 1.0045 0.02829 0.01976 -0.0667 0.4620 1.0000
7.000 1.0223 0.02906 0.02051 -0.0642 0.4231 1.0000
7.250 1.0419 0.02986 0.02117 -0.0619 0.3840 1.0000
7.500 1.0612 0.03081 0.02194 -0.0597 0.3448 1.0000
7.750 1.0754 0.03208 0.02317 -0.0571 0.3069 1.0000
8.000 1.0931 0.03342 0.02423 -0.0549 0.2705 1.0000
8.250 1.1066 0.03514 0.02595 -0.0525 0.2379 1.0000
8.500 1.1217 0.03709 0.02785 -0.0503 0.2085 1.0000
8.750 1.1372 0.03921 0.02986 -0.0483 0.1822 1.0000
9.000 1.1517 0.04140 0.03205 -0.0463 0.1590 1.0000
9.250 1.1636 0.04413 0.03490 -0.0441 0.1406 1.0000
9.500 1.1736 0.04699 0.03796 -0.0418 0.1258 1.0000
9.750 1.1848 0.05005 0.04115 -0.0399 0.1139 1.0000
10.000 1.1921 0.05318 0.04457 -0.0375 0.1054 1.0000
10.250 1.1933 0.05706 0.04879 -0.0350 0.1004 1.0000
10.500 1.1842 0.06101 0.05325 -0.0317 0.0980 1.0000
10.750 1.1722 0.06517 0.05782 -0.0287 0.0969 1.0000
11.000 1.1539 0.06922 0.06220 -0.0256 0.0966 1.0000
11.250 1.1305 0.07349 0.06673 -0.0230 0.0971 1.0000
11.500 1.1038 0.07828 0.07175 -0.0217 0.0979 1.0000
11.750 1.0762 0.08378 0.07744 -0.0220 0.0991 1.0000
12.000 1.0495 0.09011 0.08389 -0.0238 0.1003 1.0000
12.250 1.0251 0.09724 0.09110 -0.0269 0.1015 1.0000
12.500 1.0064 0.10477 0.09867 -0.0303 0.1025 1.0000
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Polar data table (+)
Polar graphs
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