AG46ct -02f rot. (ag46ct02r-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG46ct -02f rot. (ag46ct02r-il) Reynolds number: 50,000 Max Cl/Cd: 30.8 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag46ct02r-il-50000.txt Download as CSV file: xf-ag46ct02r-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG46ct -02f rot.
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5932 0.11380 0.10729 0.0225 1.0000 0.1821
-8.000 -0.5726 0.10787 0.10134 0.0250 1.0000 0.1912
-7.750 -0.5907 0.10728 0.10091 0.0187 1.0000 0.1964
-7.500 -0.5700 0.10158 0.09520 0.0220 1.0000 0.2083
-7.250 -0.5607 0.09737 0.09104 0.0222 1.0000 0.2171
-7.000 -0.5602 0.09411 0.08787 0.0197 1.0000 0.2273
-6.750 -0.5559 0.09069 0.08451 0.0171 1.0000 0.2401
-6.250 -0.5365 0.08302 0.07694 0.0169 1.0000 0.2706
-6.000 -0.5276 0.07962 0.07358 0.0163 1.0000 0.2916
-5.750 -0.5173 0.07596 0.06997 0.0176 1.0000 0.3152
-5.500 -0.5082 0.07275 0.06682 0.0188 1.0000 0.3469
-5.250 -0.4994 0.06947 0.06357 0.0213 1.0000 0.3828
-4.750 -0.4792 0.06324 0.05749 0.0294 1.0000 0.4670
-4.500 -0.3880 0.04763 0.04038 -0.0247 1.0000 0.1972
-4.250 -0.3464 0.03999 0.03187 -0.0298 1.0000 0.1335
-4.000 -0.3145 0.03537 0.02654 -0.0313 1.0000 0.1187
-3.750 -0.2823 0.03173 0.02201 -0.0318 1.0000 0.1116
-3.500 -0.2537 0.02879 0.01862 -0.0317 1.0000 0.1145
-3.250 -0.2259 0.02647 0.01607 -0.0313 1.0000 0.1229
-3.000 -0.1965 0.02407 0.01327 -0.0307 1.0000 0.1292
-2.750 -0.1689 0.02224 0.01138 -0.0300 1.0000 0.1512
-2.500 -0.1412 0.02029 0.00943 -0.0289 1.0000 0.1850
-2.250 -0.1143 0.01785 0.00768 -0.0280 1.0000 0.3003
-2.000 -0.0822 0.01394 0.00603 -0.0251 1.0000 1.0000
-1.750 -0.0562 0.01388 0.00542 -0.0246 1.0000 1.0000
-1.500 -0.0307 0.01384 0.00499 -0.0242 1.0000 1.0000
-1.250 -0.0054 0.01382 0.00462 -0.0238 1.0000 1.0000
-1.000 0.0197 0.01382 0.00436 -0.0234 1.0000 1.0000
-0.750 0.0446 0.01383 0.00418 -0.0230 1.0000 1.0000
-0.500 0.0692 0.01387 0.00406 -0.0226 1.0000 1.0000
-0.250 0.0934 0.01394 0.00398 -0.0223 1.0000 1.0000
0.000 0.1172 0.01404 0.00400 -0.0220 1.0000 1.0000
0.250 0.1404 0.01419 0.00410 -0.0217 1.0000 1.0000
0.500 0.1626 0.01442 0.00430 -0.0215 1.0000 1.0000
0.750 0.1833 0.01475 0.00461 -0.0215 1.0000 1.0000
1.000 0.2034 0.01522 0.00505 -0.0217 1.0000 1.0000
1.250 0.2231 0.01582 0.00563 -0.0222 1.0000 1.0000
1.500 0.2425 0.01654 0.00635 -0.0231 1.0000 1.0000
1.750 0.2916 0.01738 0.00727 -0.0296 0.9833 1.0000
2.000 0.3758 0.01789 0.00799 -0.0411 0.9423 1.0000
2.250 0.4446 0.01801 0.00832 -0.0480 0.9003 1.0000
2.500 0.4891 0.01810 0.00857 -0.0493 0.8577 1.0000
2.750 0.5183 0.01833 0.00883 -0.0474 0.8159 1.0000
3.000 0.5410 0.01871 0.00917 -0.0444 0.7745 1.0000
3.250 0.5617 0.01920 0.00962 -0.0411 0.7332 1.0000
3.500 0.5820 0.01982 0.01018 -0.0380 0.6911 1.0000
3.750 0.6027 0.02040 0.01081 -0.0353 0.6458 1.0000
4.000 0.6237 0.02083 0.01118 -0.0325 0.6009 1.0000
4.250 0.6451 0.02123 0.01146 -0.0297 0.5552 1.0000
4.500 0.6669 0.02175 0.01187 -0.0273 0.5061 1.0000
4.750 0.6891 0.02237 0.01232 -0.0251 0.4575 1.0000
5.000 0.7119 0.02321 0.01306 -0.0233 0.4095 1.0000
5.250 0.7349 0.02423 0.01395 -0.0218 0.3650 1.0000
5.500 0.7584 0.02544 0.01505 -0.0205 0.3261 1.0000
5.750 0.7822 0.02685 0.01641 -0.0194 0.2919 1.0000
6.000 0.8057 0.02831 0.01775 -0.0183 0.2613 1.0000
6.250 0.8297 0.03022 0.01989 -0.0175 0.2353 1.0000
6.500 0.8524 0.03211 0.02194 -0.0166 0.2098 1.0000
6.750 0.8760 0.03458 0.02444 -0.0158 0.1917 1.0000
7.000 0.8965 0.03731 0.02770 -0.0151 0.1729 1.0000
7.250 0.9166 0.04060 0.03138 -0.0144 0.1594 1.0000
7.500 0.9357 0.04422 0.03530 -0.0138 0.1490 1.0000
7.750 0.9527 0.04743 0.03883 -0.0132 0.1363 1.0000
8.000 0.9598 0.05349 0.04574 -0.0137 0.1335 1.0000
8.250 0.9620 0.06016 0.05300 -0.0149 0.1332 1.0000
8.500 0.9590 0.06723 0.06048 -0.0170 0.1343 1.0000
8.750 0.9536 0.07426 0.06774 -0.0195 0.1357 1.0000
9.000 0.9484 0.08104 0.07465 -0.0221 0.1368 1.0000
9.250 0.9446 0.08765 0.08136 -0.0245 0.1378 1.0000
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Polar data table (+)
Polar graphs
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