AG37 (ag37-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG37 (ag37-il) Reynolds number: 100,000 Max Cl/Cd: 49.26 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag37-il-100000.txt Download as CSV file: xf-ag37-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG37
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4051 0.09290 0.08827 -0.0131 1.0000 0.0925
-9.500 -0.4221 0.09001 0.08546 -0.0179 1.0000 0.0935
-9.250 -0.4393 0.08661 0.08215 -0.0231 1.0000 0.0939
-9.000 -0.3975 0.08074 0.07622 -0.0140 1.0000 0.0995
-8.750 -0.3990 0.07716 0.07268 -0.0151 1.0000 0.1033
-8.500 -0.4135 0.07367 0.06928 -0.0188 1.0000 0.1064
-8.250 -0.4354 0.06867 0.06418 -0.0310 1.0000 0.1080
-7.750 -0.4696 0.07102 0.06627 -0.0278 1.0000 0.1099
-7.500 -0.4574 0.06810 0.06340 -0.0256 1.0000 0.1143
-7.250 -0.4461 0.06322 0.05833 -0.0322 1.0000 0.1239
-7.000 -0.4329 0.06037 0.05557 -0.0298 1.0000 0.1290
-6.750 -0.4190 0.05635 0.05142 -0.0325 1.0000 0.1398
-6.500 -0.4036 0.05295 0.04787 -0.0341 1.0000 0.1531
-6.250 -0.3882 0.04997 0.04481 -0.0341 1.0000 0.1676
-6.000 -0.3733 0.04734 0.04223 -0.0329 1.0000 0.1841
-5.500 -0.3045 0.03338 0.02629 -0.0391 1.0000 0.0927
-5.250 -0.2784 0.02869 0.02105 -0.0385 1.0000 0.0760
-5.000 -0.2522 0.02540 0.01716 -0.0376 1.0000 0.0702
-4.750 -0.2264 0.02323 0.01455 -0.0367 1.0000 0.0699
-4.500 -0.2017 0.02178 0.01292 -0.0359 1.0000 0.0744
-4.250 -0.1755 0.02020 0.01104 -0.0350 1.0000 0.0764
-4.000 -0.1494 0.01898 0.00956 -0.0340 1.0000 0.0797
-3.750 -0.1245 0.01764 0.00834 -0.0335 1.0000 0.0897
-3.500 -0.0990 0.01647 0.00726 -0.0328 1.0000 0.1003
-3.250 -0.0735 0.01548 0.00640 -0.0322 1.0000 0.1259
-3.000 -0.0476 0.01223 0.00558 -0.0321 1.0000 0.6006
-2.750 -0.0179 0.01141 0.00536 -0.0306 1.0000 1.0000
-2.500 0.0053 0.01152 0.00521 -0.0299 1.0000 1.0000
-2.250 0.0282 0.01168 0.00515 -0.0294 1.0000 1.0000
-2.000 0.0508 0.01188 0.00518 -0.0289 1.0000 1.0000
-1.750 0.0731 0.01214 0.00530 -0.0285 1.0000 1.0000
-1.500 0.0949 0.01247 0.00551 -0.0282 1.0000 1.0000
-1.250 0.1328 0.01281 0.00574 -0.0312 0.9940 1.0000
-1.000 0.1926 0.01295 0.00577 -0.0380 0.9760 1.0000
-0.750 0.2522 0.01295 0.00570 -0.0445 0.9580 1.0000
-0.500 0.3070 0.01282 0.00554 -0.0497 0.9374 1.0000
-0.250 0.3545 0.01260 0.00531 -0.0531 0.9135 1.0000
0.000 0.3927 0.01240 0.00507 -0.0543 0.8842 1.0000
0.250 0.4271 0.01224 0.00484 -0.0546 0.8555 1.0000
0.500 0.4560 0.01226 0.00476 -0.0538 0.8240 1.0000
0.750 0.4823 0.01241 0.00481 -0.0527 0.7926 1.0000
1.000 0.5075 0.01262 0.00491 -0.0515 0.7625 1.0000
1.250 0.5325 0.01287 0.00504 -0.0504 0.7339 1.0000
1.500 0.5575 0.01312 0.00519 -0.0494 0.7062 1.0000
1.750 0.5826 0.01338 0.00537 -0.0484 0.6790 1.0000
2.000 0.6077 0.01363 0.00553 -0.0475 0.6524 1.0000
2.250 0.6328 0.01395 0.00573 -0.0466 0.6263 1.0000
2.500 0.6580 0.01436 0.00604 -0.0458 0.6001 1.0000
2.750 0.6831 0.01482 0.00645 -0.0451 0.5741 1.0000
3.000 0.7082 0.01529 0.00684 -0.0443 0.5487 1.0000
3.250 0.7332 0.01574 0.00722 -0.0436 0.5234 1.0000
3.500 0.7580 0.01613 0.00761 -0.0429 0.4965 1.0000
3.750 0.7827 0.01648 0.00799 -0.0422 0.4693 1.0000
4.000 0.8071 0.01676 0.00828 -0.0414 0.4412 1.0000
4.250 0.8312 0.01704 0.00854 -0.0406 0.4118 1.0000
4.500 0.8548 0.01738 0.00883 -0.0398 0.3808 1.0000
4.750 0.8779 0.01782 0.00925 -0.0390 0.3470 1.0000
5.000 0.9003 0.01835 0.00972 -0.0381 0.3100 1.0000
5.250 0.9218 0.01900 0.01029 -0.0372 0.2682 1.0000
5.500 0.9418 0.01993 0.01100 -0.0362 0.2216 1.0000
5.750 0.9610 0.02121 0.01211 -0.0350 0.1748 1.0000
6.000 0.9800 0.02268 0.01336 -0.0339 0.1419 1.0000
6.250 1.0000 0.02430 0.01490 -0.0328 0.1206 1.0000
6.500 1.0208 0.02592 0.01649 -0.0318 0.1057 1.0000
6.750 1.0421 0.02768 0.01827 -0.0310 0.0946 1.0000
7.000 1.0646 0.02999 0.02043 -0.0304 0.0865 1.0000
7.250 1.0856 0.03154 0.02239 -0.0293 0.0793 1.0000
7.500 1.1079 0.03449 0.02523 -0.0290 0.0738 1.0000
7.750 1.1264 0.03680 0.02813 -0.0275 0.0705 1.0000
8.000 1.1440 0.03904 0.03068 -0.0263 0.0660 1.0000
8.250 1.1611 0.04205 0.03377 -0.0256 0.0626 1.0000
8.500 1.1708 0.04656 0.03877 -0.0241 0.0613 1.0000
8.750 1.1750 0.05023 0.04305 -0.0219 0.0605 1.0000
9.000 1.1737 0.05417 0.04756 -0.0196 0.0596 1.0000
9.250 1.1665 0.05837 0.05225 -0.0174 0.0587 1.0000
9.500 1.1537 0.06276 0.05703 -0.0154 0.0584 1.0000
9.750 1.1348 0.06711 0.06169 -0.0134 0.0585 1.0000
10.000 1.1122 0.07163 0.06642 -0.0123 0.0589 1.0000
10.250 1.0885 0.07698 0.07194 -0.0132 0.0595 1.0000
10.500 1.0656 0.08328 0.07838 -0.0160 0.0602 1.0000
10.750 1.0451 0.09040 0.08558 -0.0196 0.0609 1.0000
11.000 1.0286 0.09796 0.09319 -0.0231 0.0615 1.0000
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Polar data table (+)
Polar graphs
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