AG19 (ag19-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG19 (ag19-il) Reynolds number: 500,000 Max Cl/Cd: 77.24 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag19-il-500000-n5.txt Download as CSV file: xf-ag19-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5350 0.09684 0.09464 0.0149 1.0000 0.0073
-7.750 -0.5301 0.09308 0.09091 0.0128 1.0000 0.0073
-7.500 -0.5254 0.08921 0.08705 0.0104 1.0000 0.0072
-7.250 -0.5198 0.08453 0.08240 0.0065 1.0000 0.0067
-7.000 -0.5078 0.07868 0.07655 0.0003 1.0000 0.0054
-6.750 -0.4940 0.07378 0.07165 -0.0054 1.0000 0.0052
-6.500 -0.4768 0.06845 0.06631 -0.0120 1.0000 0.0050
-6.250 -0.4558 0.06249 0.06032 -0.0195 1.0000 0.0049
-6.000 -0.4310 0.05580 0.05356 -0.0277 1.0000 0.0048
-5.750 -0.4024 0.04814 0.04576 -0.0361 1.0000 0.0047
-5.500 -0.3712 0.03936 0.03672 -0.0436 1.0000 0.0046
-5.250 -0.3387 0.02808 0.02485 -0.0496 1.0000 0.0048
-5.000 -0.3087 0.01936 0.01520 -0.0519 1.0000 0.0053
-4.750 -0.2813 0.01684 0.01222 -0.0522 1.0000 0.0056
-4.500 -0.2543 0.01459 0.00954 -0.0523 1.0000 0.0062
-4.250 -0.2282 0.01392 0.00878 -0.0522 1.0000 0.0069
-4.000 -0.2014 0.01272 0.00734 -0.0520 1.0000 0.0072
-3.750 -0.1746 0.01153 0.00593 -0.0516 1.0000 0.0073
-3.500 -0.1480 0.01061 0.00487 -0.0512 1.0000 0.0075
-3.250 -0.1206 0.00987 0.00403 -0.0510 0.9995 0.0078
-3.000 -0.0849 0.00921 0.00326 -0.0526 0.9929 0.0086
-2.750 -0.0493 0.00874 0.00270 -0.0542 0.9830 0.0098
-2.500 -0.0139 0.00824 0.00212 -0.0557 0.9694 0.0136
-2.250 0.0201 0.00793 0.00181 -0.0568 0.9495 0.0234
-2.000 0.0514 0.00769 0.00156 -0.0573 0.9245 0.0398
-1.750 0.0787 0.00747 0.00138 -0.0570 0.8956 0.0709
-1.500 0.1047 0.00728 0.00123 -0.0563 0.8658 0.1159
-1.250 0.1307 0.00712 0.00112 -0.0558 0.8361 0.1687
-1.000 0.1571 0.00700 0.00104 -0.0553 0.8066 0.2247
-0.750 0.1835 0.00686 0.00098 -0.0550 0.7769 0.2978
-0.500 0.2102 0.00671 0.00095 -0.0547 0.7471 0.3790
-0.250 0.2369 0.00655 0.00093 -0.0544 0.7173 0.4760
0.000 0.2634 0.00636 0.00094 -0.0541 0.6865 0.5835
0.250 0.2881 0.00600 0.00095 -0.0534 0.6539 0.7413
0.750 0.3403 0.00581 0.00091 -0.0520 0.5791 1.0000
1.000 0.3675 0.00603 0.00093 -0.0517 0.5381 1.0000
1.250 0.3946 0.00627 0.00097 -0.0516 0.4960 1.0000
1.500 0.4218 0.00652 0.00103 -0.0514 0.4542 1.0000
1.750 0.4490 0.00678 0.00112 -0.0513 0.4148 1.0000
2.000 0.4762 0.00703 0.00121 -0.0511 0.3788 1.0000
2.250 0.5034 0.00729 0.00131 -0.0510 0.3450 1.0000
2.500 0.5306 0.00754 0.00143 -0.0509 0.3141 1.0000
2.750 0.5578 0.00780 0.00156 -0.0508 0.2856 1.0000
3.000 0.5851 0.00804 0.00172 -0.0507 0.2604 1.0000
3.250 0.6122 0.00830 0.00188 -0.0505 0.2347 1.0000
3.500 0.6394 0.00854 0.00205 -0.0504 0.2139 1.0000
3.750 0.6664 0.00883 0.00224 -0.0503 0.1902 1.0000
4.000 0.6934 0.00910 0.00244 -0.0501 0.1696 1.0000
4.250 0.7203 0.00940 0.00270 -0.0500 0.1503 1.0000
4.500 0.7471 0.00971 0.00294 -0.0498 0.1300 1.0000
4.750 0.7739 0.01002 0.00321 -0.0497 0.1145 1.0000
5.000 0.8004 0.01037 0.00351 -0.0495 0.0978 1.0000
5.250 0.8270 0.01071 0.00382 -0.0493 0.0842 1.0000
5.500 0.8535 0.01108 0.00418 -0.0491 0.0720 1.0000
5.750 0.8798 0.01147 0.00455 -0.0489 0.0598 1.0000
6.000 0.9060 0.01184 0.00493 -0.0487 0.0505 1.0000
6.250 0.9321 0.01226 0.00534 -0.0485 0.0410 1.0000
6.500 0.9580 0.01271 0.00580 -0.0482 0.0329 1.0000
6.750 0.9836 0.01322 0.00631 -0.0479 0.0248 1.0000
7.000 1.0091 0.01374 0.00688 -0.0476 0.0189 1.0000
7.250 1.0343 0.01429 0.00747 -0.0473 0.0141 1.0000
7.500 1.0590 0.01501 0.00822 -0.0469 0.0099 1.0000
7.750 1.0839 0.01563 0.00894 -0.0465 0.0083 1.0000
8.000 1.1082 0.01636 0.00975 -0.0460 0.0067 1.0000
8.250 1.1313 0.01742 0.01094 -0.0454 0.0052 1.0000
8.500 1.1554 0.01807 0.01170 -0.0450 0.0045 1.0000
8.750 1.1788 0.01889 0.01264 -0.0445 0.0039 1.0000
9.000 1.2015 0.01983 0.01375 -0.0440 0.0035 1.0000
9.250 1.2230 0.02099 0.01507 -0.0433 0.0032 1.0000
9.500 1.2406 0.02293 0.01725 -0.0423 0.0028 1.0000
9.750 1.2608 0.02418 0.01870 -0.0416 0.0027 1.0000
10.000 1.2794 0.02566 0.02040 -0.0407 0.0025 1.0000
10.250 1.2962 0.02740 0.02238 -0.0397 0.0024 1.0000
10.500 1.3107 0.02938 0.02462 -0.0386 0.0022 1.0000
10.750 1.3227 0.03160 0.02712 -0.0373 0.0021 1.0000
11.000 1.3315 0.03410 0.02990 -0.0360 0.0020 1.0000
11.250 1.3362 0.03687 0.03297 -0.0346 0.0019 1.0000
11.500 1.3358 0.03993 0.03632 -0.0331 0.0019 1.0000
11.750 1.3269 0.04311 0.03974 -0.0312 0.0019 1.0000
12.000 1.3128 0.04718 0.04405 -0.0310 0.0019 1.0000
12.250 1.2970 0.05285 0.04995 -0.0341 0.0019 1.0000
12.500 1.2792 0.06090 0.05823 -0.0406 0.0019 1.0000
12.750 1.2580 0.07148 0.06902 -0.0492 0.0019 1.0000
13.000 1.2330 0.08286 0.08054 -0.0568 0.0020 1.0000
13.250 1.2055 0.09397 0.09176 -0.0630 0.0020 1.0000
13.500 1.1780 0.10472 0.10258 -0.0684 0.0021 1.0000
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Polar data table (+)
Polar graphs
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