AG45ct -02f (ag45ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG45ct -02f (ag45ct02r-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.09 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag45ct02r-il-1000000-n5.txt Download as CSV file: xf-ag45ct02r-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG45ct -02f
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.5841 0.02207 0.01893 -0.0322 1.0000 0.0033
-6.750 -0.5627 0.01826 0.01457 -0.0322 1.0000 0.0033
-6.500 -0.5383 0.01649 0.01250 -0.0320 1.0000 0.0034
-6.250 -0.5153 0.01360 0.00912 -0.0316 1.0000 0.0038
-6.000 -0.4892 0.01291 0.00830 -0.0314 1.0000 0.0039
-5.750 -0.4629 0.01234 0.00766 -0.0311 1.0000 0.0042
-5.500 -0.4363 0.01174 0.00697 -0.0309 0.9995 0.0044
-5.250 -0.4030 0.01109 0.00622 -0.0321 0.9839 0.0046
-5.000 -0.3673 0.01046 0.00546 -0.0338 0.9489 0.0049
-4.750 -0.3426 0.01016 0.00486 -0.0328 0.8658 0.0051
-4.500 -0.3187 0.01000 0.00432 -0.0317 0.7830 0.0052
-4.250 -0.2923 0.00973 0.00384 -0.0313 0.7451 0.0054
-4.000 -0.2651 0.00953 0.00351 -0.0311 0.7266 0.0056
-3.750 -0.2378 0.00916 0.00302 -0.0309 0.7143 0.0060
-3.500 -0.2102 0.00881 0.00257 -0.0307 0.7059 0.0064
-3.250 -0.1824 0.00855 0.00224 -0.0306 0.6980 0.0069
-3.000 -0.1544 0.00834 0.00198 -0.0305 0.6881 0.0078
-2.750 -0.1265 0.00817 0.00176 -0.0304 0.6771 0.0088
-2.500 -0.0985 0.00798 0.00154 -0.0303 0.6647 0.0122
-2.250 -0.0706 0.00783 0.00136 -0.0302 0.6512 0.0178
-2.000 -0.0427 0.00770 0.00121 -0.0301 0.6359 0.0276
-1.750 -0.0150 0.00752 0.00108 -0.0300 0.6200 0.0528
-1.500 0.0128 0.00734 0.00097 -0.0299 0.6029 0.0880
-1.250 0.0405 0.00718 0.00087 -0.0299 0.5843 0.1305
-1.000 0.0681 0.00702 0.00080 -0.0298 0.5653 0.1815
-0.750 0.0957 0.00686 0.00074 -0.0298 0.5460 0.2403
-0.500 0.1233 0.00670 0.00070 -0.0298 0.5260 0.3041
-0.250 0.1508 0.00655 0.00067 -0.0298 0.5058 0.3766
0.000 0.1782 0.00637 0.00066 -0.0297 0.4850 0.4605
0.250 0.2054 0.00619 0.00067 -0.0297 0.4644 0.5523
0.500 0.2323 0.00601 0.00069 -0.0295 0.4434 0.6463
0.750 0.2586 0.00582 0.00072 -0.0291 0.4227 0.7441
1.000 0.2834 0.00562 0.00076 -0.0283 0.4018 0.8422
1.250 0.3079 0.00547 0.00080 -0.0272 0.3817 0.9540
1.500 0.3442 0.00558 0.00083 -0.0290 0.3592 1.0000
1.750 0.3718 0.00573 0.00088 -0.0289 0.3400 1.0000
2.000 0.3994 0.00587 0.00093 -0.0288 0.3209 1.0000
2.250 0.4270 0.00603 0.00100 -0.0287 0.3019 1.0000
2.500 0.4547 0.00618 0.00108 -0.0286 0.2853 1.0000
2.750 0.4823 0.00634 0.00117 -0.0285 0.2675 1.0000
3.000 0.5099 0.00650 0.00126 -0.0284 0.2516 1.0000
3.250 0.5373 0.00668 0.00136 -0.0284 0.2328 1.0000
3.500 0.5648 0.00687 0.00149 -0.0283 0.2160 1.0000
3.750 0.5922 0.00707 0.00162 -0.0282 0.1974 1.0000
4.000 0.6196 0.00727 0.00176 -0.0281 0.1820 1.0000
4.250 0.6467 0.00751 0.00192 -0.0280 0.1630 1.0000
4.500 0.6740 0.00774 0.00210 -0.0279 0.1477 1.0000
4.750 0.7011 0.00799 0.00229 -0.0278 0.1311 1.0000
5.000 0.7282 0.00824 0.00248 -0.0277 0.1172 1.0000
5.250 0.7551 0.00851 0.00270 -0.0276 0.1027 1.0000
5.500 0.7820 0.00879 0.00294 -0.0274 0.0894 1.0000
5.750 0.8089 0.00908 0.00318 -0.0273 0.0776 1.0000
6.000 0.8356 0.00939 0.00345 -0.0272 0.0656 1.0000
6.250 0.8621 0.00973 0.00374 -0.0270 0.0539 1.0000
6.500 0.8885 0.01008 0.00406 -0.0269 0.0436 1.0000
6.750 0.9147 0.01046 0.00441 -0.0267 0.0346 1.0000
7.000 0.9410 0.01083 0.00476 -0.0265 0.0278 1.0000
7.250 0.9672 0.01119 0.00512 -0.0263 0.0228 1.0000
7.500 0.9931 0.01161 0.00553 -0.0261 0.0180 1.0000
7.750 1.0191 0.01198 0.00593 -0.0259 0.0151 1.0000
8.000 1.0446 0.01246 0.00641 -0.0257 0.0116 1.0000
8.250 1.0703 0.01284 0.00685 -0.0255 0.0103 1.0000
8.500 1.0956 0.01332 0.00734 -0.0252 0.0088 1.0000
8.750 1.1206 0.01386 0.00793 -0.0249 0.0073 1.0000
9.000 1.1458 0.01430 0.00843 -0.0247 0.0068 1.0000
9.250 1.1707 0.01480 0.00899 -0.0244 0.0060 1.0000
9.500 1.1950 0.01539 0.00963 -0.0241 0.0052 1.0000
9.750 1.2186 0.01610 0.01042 -0.0237 0.0046 1.0000
10.000 1.2427 0.01666 0.01105 -0.0233 0.0043 1.0000
10.250 1.2663 0.01727 0.01175 -0.0229 0.0041 1.0000
10.500 1.2895 0.01793 0.01250 -0.0225 0.0038 1.0000
10.750 1.3121 0.01864 0.01329 -0.0221 0.0035 1.0000
11.000 1.3342 0.01942 0.01414 -0.0216 0.0032 1.0000
11.250 1.3552 0.02032 0.01513 -0.0210 0.0030 1.0000
11.500 1.3741 0.02152 0.01649 -0.0203 0.0027 1.0000
11.750 1.3930 0.02262 0.01772 -0.0196 0.0026 1.0000
12.000 1.4122 0.02360 0.01881 -0.0189 0.0026 1.0000
12.250 1.4302 0.02466 0.02000 -0.0182 0.0025 1.0000
12.500 1.4469 0.02582 0.02129 -0.0174 0.0024 1.0000
12.750 1.4623 0.02704 0.02264 -0.0166 0.0023 1.0000
13.000 1.4761 0.02834 0.02406 -0.0156 0.0022 1.0000
13.250 1.4880 0.02973 0.02558 -0.0146 0.0021 1.0000
13.500 1.4967 0.03125 0.02723 -0.0135 0.0020 1.0000
13.750 1.4994 0.03296 0.02906 -0.0118 0.0019 1.0000
14.000 1.4986 0.03519 0.03143 -0.0110 0.0018 1.0000
14.250 1.4953 0.03832 0.03472 -0.0119 0.0018 1.0000
14.500 1.4899 0.04255 0.03910 -0.0143 0.0018 1.0000
14.750 1.4810 0.04767 0.04438 -0.0175 0.0017 1.0000
15.000 1.4665 0.05407 0.05094 -0.0216 0.0017 1.0000
15.250 1.4452 0.06195 0.05900 -0.0265 0.0017 1.0000
15.500 1.4165 0.07131 0.06854 -0.0320 0.0017 1.0000
15.750 1.3806 0.08207 0.07947 -0.0378 0.0018 1.0000
16.000 1.3358 0.09451 0.09206 -0.0442 0.0019 1.0000
16.250 1.2933 0.10671 0.10441 -0.0502 0.0020 1.0000
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Polar data table (+)
Polar graphs
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