AG19 (ag19-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG19 (ag19-il) Reynolds number: 200,000 Max Cl/Cd: 60.39 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag19-il-200000-n5.txt Download as CSV file: xf-ag19-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.4199 0.07386 0.07068 -0.0026 1.0000 0.0153
-7.000 -0.4193 0.06970 0.06656 -0.0039 1.0000 0.0141
-6.750 -0.4178 0.06516 0.06205 -0.0064 1.0000 0.0133
-6.500 -0.4130 0.05965 0.05656 -0.0109 1.0000 0.0124
-6.250 -0.4051 0.05292 0.04983 -0.0174 1.0000 0.0115
-6.000 -0.3907 0.04374 0.04058 -0.0269 1.0000 0.0105
-5.750 -0.3728 0.03688 0.03361 -0.0332 1.0000 0.0104
-5.500 -0.3539 0.03095 0.02752 -0.0382 1.0000 0.0108
-5.250 -0.3519 0.04120 0.03728 -0.0432 1.0000 0.0117
-5.000 -0.3253 0.03741 0.03328 -0.0459 1.0000 0.0135
-4.750 -0.2957 0.03156 0.02699 -0.0488 1.0000 0.0135
-4.500 -0.2660 0.02608 0.02092 -0.0507 1.0000 0.0129
-4.250 -0.2368 0.02189 0.01604 -0.0516 1.0000 0.0126
-4.000 -0.2084 0.01901 0.01260 -0.0517 1.0000 0.0126
-3.750 -0.1807 0.01695 0.01013 -0.0515 1.0000 0.0128
-3.500 -0.1535 0.01537 0.00826 -0.0512 1.0000 0.0133
-3.250 -0.1266 0.01410 0.00679 -0.0508 1.0000 0.0143
-3.000 -0.0999 0.01308 0.00563 -0.0504 1.0000 0.0157
-2.750 -0.0735 0.01225 0.00474 -0.0501 1.0000 0.0197
-2.500 -0.0469 0.01164 0.00404 -0.0498 1.0000 0.0242
-2.250 -0.0199 0.01102 0.00337 -0.0495 1.0000 0.0329
-2.000 0.0068 0.01054 0.00293 -0.0493 1.0000 0.0545
-1.500 0.0706 0.00955 0.00249 -0.0516 0.9912 0.1991
-1.250 0.1080 0.00903 0.00234 -0.0539 0.9779 0.3191
-1.000 0.1435 0.00849 0.00226 -0.0556 0.9620 0.4649
-0.750 0.1760 0.00781 0.00219 -0.0564 0.9434 0.6511
-0.500 0.2082 0.00705 0.00202 -0.0563 0.9215 1.0000
-0.250 0.2402 0.00708 0.00188 -0.0567 0.8955 1.0000
0.000 0.2693 0.00713 0.00179 -0.0565 0.8667 1.0000
0.250 0.2964 0.00722 0.00171 -0.0559 0.8360 1.0000
0.500 0.3225 0.00734 0.00167 -0.0550 0.8043 1.0000
0.750 0.3484 0.00748 0.00164 -0.0542 0.7711 1.0000
1.000 0.3743 0.00765 0.00163 -0.0534 0.7368 1.0000
1.250 0.4003 0.00784 0.00164 -0.0527 0.7005 1.0000
1.500 0.4263 0.00806 0.00167 -0.0521 0.6616 1.0000
1.750 0.4523 0.00830 0.00174 -0.0514 0.6193 1.0000
2.000 0.4782 0.00858 0.00181 -0.0509 0.5740 1.0000
2.250 0.5042 0.00890 0.00190 -0.0504 0.5262 1.0000
2.500 0.5302 0.00924 0.00203 -0.0499 0.4788 1.0000
2.750 0.5563 0.00959 0.00218 -0.0496 0.4338 1.0000
3.000 0.5825 0.00996 0.00241 -0.0492 0.3913 1.0000
3.250 0.6088 0.01034 0.00263 -0.0490 0.3529 1.0000
3.500 0.6351 0.01070 0.00286 -0.0487 0.3176 1.0000
3.750 0.6615 0.01109 0.00313 -0.0485 0.2858 1.0000
4.000 0.6878 0.01146 0.00341 -0.0483 0.2559 1.0000
4.250 0.7142 0.01185 0.00377 -0.0481 0.2282 1.0000
4.500 0.7404 0.01226 0.00411 -0.0479 0.2020 1.0000
4.750 0.7665 0.01270 0.00448 -0.0476 0.1765 1.0000
5.000 0.7926 0.01313 0.00489 -0.0474 0.1540 1.0000
5.250 0.8185 0.01362 0.00533 -0.0471 0.1322 1.0000
5.500 0.8442 0.01413 0.00587 -0.0469 0.1138 1.0000
5.750 0.8698 0.01468 0.00640 -0.0466 0.0970 1.0000
6.000 0.8953 0.01523 0.00698 -0.0463 0.0817 1.0000
6.250 0.9205 0.01584 0.00763 -0.0459 0.0693 1.0000
6.500 0.9455 0.01649 0.00831 -0.0456 0.0567 1.0000
6.750 0.9701 0.01724 0.00909 -0.0452 0.0464 1.0000
7.000 0.9943 0.01807 0.00999 -0.0448 0.0361 1.0000
7.250 1.0187 0.01886 0.01093 -0.0443 0.0289 1.0000
7.500 1.0420 0.01986 0.01203 -0.0438 0.0223 1.0000
7.750 1.0645 0.02106 0.01335 -0.0431 0.0178 1.0000
8.000 1.0858 0.02251 0.01501 -0.0423 0.0148 1.0000
8.250 1.1083 0.02353 0.01619 -0.0417 0.0119 1.0000
8.500 1.1276 0.02528 0.01812 -0.0409 0.0103 1.0000
8.750 1.1438 0.02776 0.02088 -0.0396 0.0094 1.0000
9.000 1.1612 0.02992 0.02336 -0.0385 0.0088 1.0000
9.250 1.1763 0.03252 0.02639 -0.0373 0.0083 1.0000
9.500 1.1892 0.03530 0.02956 -0.0360 0.0078 1.0000
9.750 1.2018 0.03763 0.03221 -0.0351 0.0071 1.0000
10.000 1.2145 0.03943 0.03423 -0.0343 0.0064 1.0000
10.250 1.2229 0.04164 0.03664 -0.0335 0.0059 1.0000
10.500 1.2197 0.04543 0.04076 -0.0323 0.0055 1.0000
10.750 1.2074 0.04964 0.04530 -0.0309 0.0054 1.0000
11.000 1.1909 0.05420 0.05013 -0.0310 0.0054 1.0000
11.250 1.1754 0.05975 0.05593 -0.0340 0.0054 1.0000
11.500 1.1615 0.06660 0.06300 -0.0394 0.0054 1.0000
11.750 1.1483 0.07473 0.07132 -0.0463 0.0055 1.0000
12.000 1.1329 0.08421 0.08099 -0.0535 0.0056 1.0000
12.250 1.0397 0.11517 0.11219 -0.0709 0.0083 1.0000
12.500 1.0148 0.12682 0.12380 -0.0764 0.0086 1.0000
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Polar data table (+)
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