AG19 (ag19-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG19 (ag19-il) Reynolds number: 50,000 Max Cl/Cd: 36.3 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag19-il-50000.txt Download as CSV file: xf-ag19-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG19
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5449 0.11263 0.10612 0.0109 1.0000 0.1598
-7.750 -0.5225 0.10592 0.09937 0.0143 1.0000 0.1689
-7.500 -0.5327 0.10550 0.09910 0.0073 1.0000 0.1735
-7.250 -0.5132 0.09940 0.09299 0.0117 1.0000 0.1832
-7.000 -0.5093 0.09609 0.08976 0.0090 1.0000 0.1900
-6.750 -0.5057 0.09405 0.08779 0.0020 1.0000 0.2008
-6.500 -0.4926 0.08943 0.08320 0.0047 1.0000 0.2131
-6.250 -0.4832 0.08599 0.07981 0.0023 1.0000 0.2273
-6.000 -0.4732 0.08238 0.07620 -0.0001 1.0000 0.2429
-5.750 -0.4605 0.07836 0.07222 0.0033 1.0000 0.2615
-5.500 -0.4502 0.07522 0.06913 0.0000 1.0000 0.2846
-5.250 -0.4374 0.07161 0.06557 0.0022 1.0000 0.3068
-5.000 -0.4253 0.06811 0.06212 0.0026 1.0000 0.3306
-4.750 -0.4131 0.06483 0.05890 0.0035 1.0000 0.3597
-4.500 -0.4023 0.06171 0.05584 0.0046 1.0000 0.3957
-4.250 -0.3922 0.05867 0.05288 0.0077 1.0000 0.4363
-4.000 -0.3829 0.05554 0.04984 0.0128 1.0000 0.4794
-3.750 -0.2166 0.03559 0.02692 -0.0505 1.0000 0.1182
-3.500 -0.1869 0.03194 0.02290 -0.0514 1.0000 0.1156
-3.250 -0.1548 0.02890 0.01915 -0.0523 1.0000 0.1197
-3.000 -0.1261 0.02615 0.01616 -0.0523 1.0000 0.1238
-2.750 -0.0957 0.02380 0.01323 -0.0519 1.0000 0.1307
-2.500 -0.0684 0.02199 0.01134 -0.0515 1.0000 0.1561
-2.250 -0.0407 0.02006 0.00932 -0.0505 1.0000 0.1891
-2.000 -0.0121 0.01806 0.00774 -0.0499 1.0000 0.2872
-1.750 0.0028 0.01382 0.00634 -0.0447 1.0000 1.0000
-1.500 0.0325 0.01383 0.00544 -0.0449 1.0000 1.0000
-1.250 0.0591 0.01385 0.00493 -0.0446 1.0000 1.0000
-1.000 0.0850 0.01390 0.00461 -0.0444 1.0000 1.0000
-0.750 0.1106 0.01396 0.00439 -0.0441 1.0000 1.0000
-0.500 0.1360 0.01405 0.00425 -0.0438 1.0000 1.0000
-0.250 0.1610 0.01417 0.00417 -0.0435 1.0000 1.0000
0.000 0.1858 0.01431 0.00414 -0.0433 1.0000 1.0000
0.250 0.2103 0.01448 0.00420 -0.0430 1.0000 1.0000
0.500 0.2346 0.01470 0.00433 -0.0428 1.0000 1.0000
0.750 0.2586 0.01495 0.00453 -0.0427 1.0000 1.0000
1.000 0.2825 0.01526 0.00481 -0.0427 1.0000 1.0000
1.250 0.3060 0.01563 0.00517 -0.0428 1.0000 1.0000
1.500 0.3289 0.01607 0.00563 -0.0430 1.0000 1.0000
1.750 0.3513 0.01661 0.00621 -0.0434 1.0000 1.0000
2.000 0.3728 0.01728 0.00694 -0.0440 1.0000 1.0000
2.250 0.3932 0.01811 0.00787 -0.0449 1.0000 1.0000
2.500 0.4548 0.01906 0.00907 -0.0535 0.9745 1.0000
2.750 0.5478 0.01926 0.00968 -0.0654 0.9220 1.0000
3.000 0.6094 0.01896 0.00969 -0.0690 0.8668 1.0000
3.250 0.6439 0.01877 0.00970 -0.0668 0.8097 1.0000
3.500 0.6669 0.01878 0.00968 -0.0626 0.7514 1.0000
3.750 0.6866 0.01905 0.00983 -0.0584 0.6889 1.0000
4.000 0.7067 0.01947 0.01003 -0.0546 0.6271 1.0000
4.250 0.7276 0.02013 0.01056 -0.0517 0.5635 1.0000
4.500 0.7495 0.02096 0.01111 -0.0492 0.5047 1.0000
4.750 0.7719 0.02201 0.01190 -0.0473 0.4489 1.0000
5.000 0.7947 0.02322 0.01294 -0.0457 0.3971 1.0000
5.250 0.8180 0.02459 0.01417 -0.0443 0.3513 1.0000
5.500 0.8413 0.02607 0.01556 -0.0430 0.3099 1.0000
5.750 0.8650 0.02771 0.01726 -0.0419 0.2744 1.0000
6.000 0.8887 0.02955 0.01910 -0.0409 0.2436 1.0000
6.250 0.9120 0.03153 0.02121 -0.0399 0.2157 1.0000
6.500 0.9353 0.03372 0.02352 -0.0389 0.1920 1.0000
6.750 0.9572 0.03658 0.02685 -0.0379 0.1720 1.0000
7.000 0.9787 0.03906 0.02944 -0.0369 0.1527 1.0000
7.250 0.9968 0.04349 0.03461 -0.0360 0.1427 1.0000
7.500 1.0140 0.04653 0.03791 -0.0350 0.1274 1.0000
7.750 1.0268 0.05155 0.04346 -0.0344 0.1210 1.0000
8.000 1.0321 0.05795 0.05057 -0.0344 0.1197 1.0000
8.250 1.0325 0.06472 0.05797 -0.0350 0.1201 1.0000
8.500 1.0286 0.07156 0.06507 -0.0364 0.1210 1.0000
8.750 1.0224 0.07829 0.07202 -0.0381 0.1222 1.0000
9.000 1.0159 0.08486 0.07872 -0.0400 0.1231 1.0000
9.250 1.0102 0.09136 0.08533 -0.0420 0.1244 1.0000
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Polar data table (+)
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