AG10 (ag10-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG10 (ag10-il) Reynolds number: 50,000 Max Cl/Cd: 30.96 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag10-il-50000-n5.txt Download as CSV file: xf-ag10-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG10
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6173 0.12378 0.11673 0.0283 1.0000 0.0891
-8.750 -0.6205 0.12164 0.11467 0.0241 1.0000 0.0900
-8.500 -0.6226 0.11912 0.11223 0.0197 1.0000 0.0904
-8.250 -0.6084 0.11283 0.10596 0.0218 1.0000 0.0916
-8.000 -0.5974 0.10824 0.10137 0.0226 1.0000 0.0935
-7.750 -0.5907 0.10448 0.09762 0.0216 1.0000 0.0953
-7.500 -0.5851 0.10092 0.09409 0.0198 1.0000 0.0976
-7.250 -0.5786 0.09731 0.09053 0.0158 1.0000 0.1013
-7.000 -0.5704 0.09410 0.08729 0.0034 1.0000 0.1047
-6.750 -0.5601 0.08898 0.08224 0.0054 1.0000 0.1066
-6.500 -0.5482 0.08506 0.07834 0.0065 1.0000 0.1107
-6.000 -0.5053 0.07142 0.06435 -0.0089 1.0000 0.0611
-5.750 -0.4885 0.06685 0.05972 -0.0110 1.0000 0.0580
-5.250 -0.4360 0.05443 0.04663 -0.0220 1.0000 0.0501
-5.000 -0.4127 0.04997 0.04194 -0.0241 1.0000 0.0496
-4.750 -0.3851 0.04511 0.03660 -0.0270 1.0000 0.0502
-4.500 -0.3605 0.04150 0.03274 -0.0284 1.0000 0.0524
-4.250 -0.3341 0.03820 0.02911 -0.0295 1.0000 0.0540
-4.000 -0.3052 0.03460 0.02502 -0.0306 1.0000 0.0547
-3.750 -0.2764 0.03168 0.02162 -0.0313 1.0000 0.0577
-3.500 -0.2462 0.02887 0.01810 -0.0317 1.0000 0.0620
-3.250 -0.2179 0.02646 0.01531 -0.0317 1.0000 0.0650
-3.000 -0.1903 0.02488 0.01351 -0.0316 1.0000 0.0722
-2.750 -0.1620 0.02309 0.01138 -0.0312 1.0000 0.0784
-2.500 -0.1345 0.02186 0.00993 -0.0307 1.0000 0.0895
-2.250 -0.1077 0.02065 0.00863 -0.0301 1.0000 0.1017
-2.000 -0.0799 0.01963 0.00746 -0.0297 1.0000 0.1193
-1.750 -0.0530 0.01867 0.00659 -0.0293 1.0000 0.1443
-1.500 -0.0262 0.01775 0.00582 -0.0290 1.0000 0.1830
-1.250 0.0001 0.01671 0.00517 -0.0288 1.0000 0.2578
-1.000 0.0235 0.01377 0.00459 -0.0270 1.0000 1.0000
-0.750 0.0501 0.01377 0.00418 -0.0264 1.0000 1.0000
-0.500 0.0762 0.01379 0.00392 -0.0260 1.0000 1.0000
-0.250 0.1021 0.01381 0.00374 -0.0255 1.0000 1.0000
0.000 0.1278 0.01385 0.00364 -0.0250 1.0000 1.0000
0.250 0.1532 0.01391 0.00360 -0.0246 1.0000 1.0000
0.500 0.1785 0.01398 0.00361 -0.0241 1.0000 1.0000
0.750 0.2035 0.01407 0.00369 -0.0236 1.0000 1.0000
1.000 0.2282 0.01419 0.00381 -0.0232 1.0000 1.0000
1.250 0.2527 0.01433 0.00400 -0.0228 1.0000 1.0000
1.500 0.2770 0.01450 0.00426 -0.0224 1.0000 1.0000
1.750 0.3155 0.01471 0.00460 -0.0250 0.9783 1.0000
2.000 0.3693 0.01487 0.00487 -0.0298 0.9147 1.0000
2.250 0.4135 0.01504 0.00506 -0.0319 0.8284 1.0000
2.500 0.4438 0.01538 0.00522 -0.0308 0.7342 1.0000
2.750 0.4670 0.01590 0.00540 -0.0285 0.6473 1.0000
3.000 0.4896 0.01653 0.00568 -0.0266 0.5733 1.0000
3.250 0.5131 0.01719 0.00606 -0.0252 0.5117 1.0000
3.500 0.5375 0.01787 0.00656 -0.0242 0.4596 1.0000
3.750 0.5624 0.01856 0.00709 -0.0234 0.4139 1.0000
4.000 0.5875 0.01926 0.00767 -0.0227 0.3732 1.0000
4.250 0.6130 0.01996 0.00833 -0.0222 0.3345 1.0000
4.500 0.6384 0.02070 0.00905 -0.0217 0.2985 1.0000
4.750 0.6643 0.02146 0.00984 -0.0213 0.2628 1.0000
5.000 0.6898 0.02230 0.01066 -0.0210 0.2295 1.0000
5.250 0.7149 0.02323 0.01154 -0.0206 0.1978 1.0000
5.500 0.7400 0.02426 0.01266 -0.0202 0.1669 1.0000
5.750 0.7645 0.02545 0.01386 -0.0197 0.1390 1.0000
6.000 0.7884 0.02681 0.01523 -0.0193 0.1152 1.0000
6.250 0.8125 0.02843 0.01704 -0.0187 0.0956 1.0000
6.500 0.8360 0.03022 0.01900 -0.0181 0.0811 1.0000
6.750 0.8590 0.03227 0.02124 -0.0175 0.0705 1.0000
7.000 0.8808 0.03431 0.02335 -0.0170 0.0626 1.0000
7.250 0.9030 0.03718 0.02679 -0.0163 0.0566 1.0000
7.500 0.9228 0.03955 0.02924 -0.0159 0.0521 1.0000
7.750 0.9407 0.04350 0.03401 -0.0154 0.0482 1.0000
8.000 0.9553 0.04774 0.03883 -0.0152 0.0462 1.0000
8.250 0.9669 0.05205 0.04361 -0.0151 0.0446 1.0000
8.500 0.9773 0.05573 0.04757 -0.0152 0.0429 1.0000
8.750 0.9818 0.06038 0.05251 -0.0156 0.0416 1.0000
9.000 0.9759 0.06667 0.05929 -0.0173 0.0413 1.0000
9.250 0.9653 0.07305 0.06599 -0.0198 0.0413 1.0000
9.500 0.9516 0.07939 0.07250 -0.0231 0.0414 1.0000
9.750 0.9376 0.08596 0.07912 -0.0277 0.0418 1.0000
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Polar data table (+)
Polar graphs
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