AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG45c -03f (ag45c03-il) Reynolds number: 50,000 Max Cl/Cd: 34.89 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag45c03-il-50000-n5.txt Download as CSV file: xf-ag45c03-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG45c -03f
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4566 0.10796 0.10173 0.0100 1.0000 0.1020
-7.750 -0.4640 0.10481 0.09866 0.0072 1.0000 0.1029
-7.500 -0.4673 0.10113 0.09503 0.0049 1.0000 0.1031
-7.250 -0.4498 0.09257 0.08637 0.0047 1.0000 0.0603
-7.000 -0.4463 0.08830 0.08210 0.0041 1.0000 0.0578
-6.750 -0.4463 0.08386 0.07771 0.0024 1.0000 0.0556
-6.500 -0.5382 0.08937 0.08295 0.0041 1.0000 0.0478
-6.250 -0.5295 0.08493 0.07854 0.0014 1.0000 0.0465
-6.000 -0.5196 0.08014 0.07376 -0.0027 1.0000 0.0456
-5.750 -0.5079 0.07510 0.06870 -0.0072 1.0000 0.0448
-5.500 -0.4944 0.06991 0.06346 -0.0117 1.0000 0.0443
-5.250 -0.4789 0.06463 0.05803 -0.0161 1.0000 0.0439
-5.000 -0.4614 0.05934 0.05257 -0.0202 1.0000 0.0435
-4.750 -0.4418 0.05411 0.04710 -0.0237 1.0000 0.0430
-4.500 -0.4202 0.04893 0.04159 -0.0267 1.0000 0.0422
-4.250 -0.3966 0.04397 0.03618 -0.0291 1.0000 0.0414
-4.000 -0.3716 0.03956 0.03127 -0.0306 1.0000 0.0410
-3.750 -0.3455 0.03576 0.02693 -0.0316 1.0000 0.0413
-3.500 -0.3187 0.03249 0.02315 -0.0320 1.0000 0.0421
-3.250 -0.2914 0.02988 0.02006 -0.0321 1.0000 0.0453
-3.000 -0.2628 0.02756 0.01711 -0.0319 1.0000 0.0493
-2.750 -0.2364 0.02534 0.01472 -0.0316 1.0000 0.0527
-2.500 -0.2093 0.02363 0.01278 -0.0310 1.0000 0.0582
-2.250 -0.1826 0.02218 0.01122 -0.0305 1.0000 0.0687
-2.000 -0.1557 0.02078 0.00972 -0.0299 1.0000 0.0821
-1.750 -0.1286 0.01951 0.00847 -0.0296 1.0000 0.1099
-1.500 -0.1019 0.01812 0.00743 -0.0297 1.0000 0.1799
-1.250 -0.0775 0.01649 0.00675 -0.0297 1.0000 0.3524
-1.000 -0.0650 0.01464 0.00655 -0.0254 1.0000 0.7102
-0.750 -0.0234 0.01402 0.00590 -0.0269 1.0000 1.0000
-0.500 0.0015 0.01403 0.00558 -0.0267 1.0000 1.0000
-0.250 0.0255 0.01408 0.00536 -0.0266 1.0000 1.0000
0.000 0.0525 0.01420 0.00526 -0.0272 0.9928 1.0000
0.250 0.0991 0.01436 0.00512 -0.0314 0.9526 1.0000
0.500 0.1434 0.01452 0.00499 -0.0347 0.9147 1.0000
0.750 0.1833 0.01469 0.00492 -0.0369 0.8790 1.0000
1.000 0.2180 0.01489 0.00488 -0.0379 0.8468 1.0000
1.250 0.2481 0.01512 0.00487 -0.0378 0.8181 1.0000
1.500 0.2754 0.01540 0.00493 -0.0372 0.7924 1.0000
1.750 0.3016 0.01570 0.00503 -0.0363 0.7694 1.0000
2.000 0.3273 0.01603 0.00520 -0.0355 0.7473 1.0000
2.250 0.3529 0.01639 0.00540 -0.0346 0.7271 1.0000
2.500 0.3786 0.01677 0.00566 -0.0338 0.7071 1.0000
2.750 0.4044 0.01715 0.00597 -0.0332 0.6860 1.0000
3.000 0.4301 0.01749 0.00627 -0.0326 0.6655 1.0000
3.250 0.4559 0.01780 0.00660 -0.0320 0.6444 1.0000
3.500 0.4815 0.01808 0.00686 -0.0313 0.6242 1.0000
3.750 0.5072 0.01836 0.00713 -0.0306 0.6035 1.0000
4.000 0.5327 0.01863 0.00739 -0.0298 0.5826 1.0000
4.250 0.5583 0.01890 0.00767 -0.0291 0.5613 1.0000
4.500 0.5837 0.01918 0.00801 -0.0283 0.5397 1.0000
4.750 0.6091 0.01949 0.00834 -0.0276 0.5169 1.0000
5.000 0.6343 0.01981 0.00864 -0.0268 0.4947 1.0000
5.250 0.6599 0.02017 0.00906 -0.0262 0.4701 1.0000
5.500 0.6852 0.02056 0.00955 -0.0255 0.4452 1.0000
5.750 0.7104 0.02099 0.01000 -0.0249 0.4200 1.0000
6.000 0.7353 0.02145 0.01050 -0.0242 0.3944 1.0000
6.250 0.7600 0.02195 0.01103 -0.0236 0.3682 1.0000
6.500 0.7846 0.02253 0.01171 -0.0230 0.3413 1.0000
6.750 0.8088 0.02318 0.01242 -0.0224 0.3141 1.0000
7.000 0.8327 0.02392 0.01322 -0.0219 0.2873 1.0000
7.250 0.8563 0.02475 0.01412 -0.0214 0.2612 1.0000
7.500 0.8793 0.02568 0.01510 -0.0209 0.2357 1.0000
7.750 0.9018 0.02671 0.01623 -0.0204 0.2122 1.0000
8.000 0.9237 0.02784 0.01742 -0.0198 0.1896 1.0000
8.250 0.9452 0.02911 0.01882 -0.0194 0.1674 1.0000
8.500 0.9657 0.03049 0.02024 -0.0188 0.1485 1.0000
8.750 0.9858 0.03204 0.02196 -0.0183 0.1294 1.0000
9.000 1.0050 0.03380 0.02388 -0.0177 0.1136 1.0000
9.250 1.0230 0.03560 0.02589 -0.0171 0.0988 1.0000
9.500 1.0405 0.03781 0.02831 -0.0164 0.0878 1.0000
9.750 1.0561 0.03998 0.03066 -0.0158 0.0772 1.0000
10.000 1.0714 0.04230 0.03307 -0.0151 0.0700 1.0000
10.250 1.0839 0.04550 0.03676 -0.0144 0.0634 1.0000
10.500 1.0956 0.04771 0.03896 -0.0139 0.0576 1.0000
10.750 1.1014 0.05180 0.04362 -0.0134 0.0542 1.0000
11.000 1.1024 0.05611 0.04841 -0.0132 0.0519 1.0000
11.250 1.0994 0.06023 0.05286 -0.0134 0.0498 1.0000
11.500 1.0940 0.06393 0.05675 -0.0136 0.0480 1.0000
11.750 1.0925 0.06700 0.05981 -0.0138 0.0459 1.0000
12.000 1.0768 0.07243 0.06543 -0.0164 0.0456 1.0000
12.250 1.0591 0.07884 0.07204 -0.0206 0.0457 1.0000
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Polar data table (+)
Polar graphs
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