AG09 (ag09-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG09 (ag09-il) Reynolds number: 50,000 Max Cl/Cd: 32.91 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag09-il-50000-n5.txt Download as CSV file: xf-ag09-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG09
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5785 0.11035 0.10356 0.0213 1.0000 0.0902
-8.000 -0.5778 0.10741 0.10069 0.0179 1.0000 0.0929
-7.750 -0.5782 0.10471 0.09807 0.0113 1.0000 0.0943
-7.500 -0.5711 0.10098 0.09435 0.0045 1.0000 0.0948
-7.250 -0.5610 0.09609 0.08951 0.0027 1.0000 0.0953
-7.000 -0.5502 0.09129 0.08473 0.0038 1.0000 0.0964
-6.500 -0.5127 0.07761 0.07075 -0.0112 1.0000 0.0543
-6.250 -0.4979 0.07299 0.06609 -0.0134 1.0000 0.0540
-6.000 -0.4816 0.06836 0.06139 -0.0159 1.0000 0.0536
-5.750 -0.4642 0.06383 0.05674 -0.0182 1.0000 0.0528
-5.500 -0.4447 0.05920 0.05198 -0.0208 1.0000 0.0515
-5.250 -0.4223 0.05436 0.04694 -0.0239 1.0000 0.0503
-5.000 -0.3976 0.04947 0.04176 -0.0269 1.0000 0.0495
-4.750 -0.3715 0.04472 0.03664 -0.0295 1.0000 0.0491
-4.500 -0.3439 0.04033 0.03177 -0.0316 1.0000 0.0505
-4.250 -0.3143 0.03608 0.02679 -0.0333 1.0000 0.0536
-4.000 -0.2868 0.03259 0.02280 -0.0341 1.0000 0.0557
-3.750 -0.2599 0.02995 0.01982 -0.0343 1.0000 0.0580
-3.500 -0.2320 0.02765 0.01705 -0.0344 1.0000 0.0631
-3.250 -0.2040 0.02555 0.01452 -0.0343 1.0000 0.0705
-3.000 -0.1763 0.02371 0.01236 -0.0339 1.0000 0.0768
-2.750 -0.1493 0.02238 0.01084 -0.0335 1.0000 0.0895
-2.500 -0.1224 0.02099 0.00926 -0.0329 1.0000 0.1011
-2.250 -0.0951 0.02003 0.00808 -0.0324 1.0000 0.1222
-2.000 -0.0682 0.01901 0.00706 -0.0319 1.0000 0.1428
-1.750 -0.0418 0.01816 0.00625 -0.0316 1.0000 0.1742
-1.500 -0.0156 0.01730 0.00555 -0.0313 1.0000 0.2191
-1.250 0.0098 0.01616 0.00492 -0.0311 1.0000 0.3124
-1.000 0.0349 0.01375 0.00440 -0.0293 1.0000 1.0000
-0.750 0.0606 0.01376 0.00406 -0.0288 1.0000 1.0000
-0.500 0.0859 0.01379 0.00384 -0.0283 1.0000 1.0000
-0.250 0.1109 0.01384 0.00370 -0.0278 1.0000 1.0000
0.000 0.1356 0.01390 0.00361 -0.0272 1.0000 1.0000
0.250 0.1600 0.01398 0.00359 -0.0267 1.0000 1.0000
0.500 0.1843 0.01409 0.00364 -0.0262 1.0000 1.0000
0.750 0.2083 0.01422 0.00375 -0.0258 1.0000 1.0000
1.000 0.2320 0.01439 0.00392 -0.0254 1.0000 1.0000
1.250 0.2553 0.01460 0.00416 -0.0251 1.0000 1.0000
1.500 0.2984 0.01484 0.00446 -0.0286 0.9777 1.0000
1.750 0.3495 0.01501 0.00475 -0.0332 0.9378 1.0000
2.000 0.3943 0.01514 0.00496 -0.0360 0.8899 1.0000
2.250 0.4319 0.01529 0.00513 -0.0369 0.8351 1.0000
2.500 0.4619 0.01551 0.00529 -0.0361 0.7761 1.0000
2.750 0.4871 0.01582 0.00551 -0.0343 0.7158 1.0000
3.000 0.5104 0.01622 0.00574 -0.0323 0.6552 1.0000
3.250 0.5335 0.01669 0.00602 -0.0305 0.5967 1.0000
3.500 0.5569 0.01724 0.00638 -0.0290 0.5413 1.0000
3.750 0.5805 0.01784 0.00680 -0.0278 0.4905 1.0000
4.000 0.6047 0.01848 0.00738 -0.0268 0.4437 1.0000
4.250 0.6292 0.01916 0.00797 -0.0260 0.4014 1.0000
4.500 0.6537 0.01988 0.00862 -0.0253 0.3628 1.0000
4.750 0.6786 0.02062 0.00936 -0.0247 0.3258 1.0000
5.000 0.7038 0.02142 0.01023 -0.0242 0.2903 1.0000
5.250 0.7285 0.02226 0.01109 -0.0237 0.2554 1.0000
5.500 0.7529 0.02317 0.01204 -0.0232 0.2198 1.0000
5.750 0.7765 0.02418 0.01302 -0.0227 0.1841 1.0000
6.000 0.8000 0.02536 0.01425 -0.0222 0.1469 1.0000
6.250 0.8225 0.02683 0.01572 -0.0216 0.1146 1.0000
6.500 0.8446 0.02852 0.01740 -0.0211 0.0892 1.0000
6.750 0.8669 0.03054 0.01963 -0.0202 0.0726 1.0000
7.000 0.8883 0.03273 0.02197 -0.0194 0.0618 1.0000
7.250 0.9093 0.03502 0.02447 -0.0186 0.0541 1.0000
7.500 0.9297 0.03783 0.02772 -0.0178 0.0479 1.0000
7.750 0.9487 0.04101 0.03140 -0.0170 0.0446 1.0000
8.000 0.9654 0.04425 0.03492 -0.0164 0.0421 1.0000
8.250 0.9780 0.04843 0.03961 -0.0160 0.0400 1.0000
8.500 0.9854 0.05334 0.04523 -0.0159 0.0381 1.0000
8.750 0.9872 0.05859 0.05104 -0.0163 0.0369 1.0000
9.000 0.9830 0.06424 0.05713 -0.0173 0.0364 1.0000
9.250 0.9724 0.07032 0.06353 -0.0194 0.0364 1.0000
9.500 0.9558 0.07668 0.07009 -0.0225 0.0369 1.0000
9.750 0.9378 0.08416 0.07764 -0.0284 0.0377 1.0000
10.000 0.9238 0.09278 0.08627 -0.0354 0.0386 1.0000
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Polar data table (+)
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