AG46ct -02f rot. (ag46ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
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Airfoil: AG46ct -02f rot. (ag46ct02r-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.21 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag46ct02r-il-1000000-n5.txt Download as CSV file: xf-ag46ct02r-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG46ct -02f rot.
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6071 0.09699 0.09544 0.0243 1.0000 0.0044
-8.250 -0.6045 0.09287 0.09134 0.0220 1.0000 0.0044
-8.000 -0.6033 0.08829 0.08677 0.0191 1.0000 0.0043
-7.500 -0.5910 0.07977 0.07828 0.0106 1.0000 0.0046
-6.000 -0.4960 0.01691 0.01307 -0.0304 1.0000 0.0035
-5.750 -0.4711 0.01445 0.01019 -0.0302 1.0000 0.0036
-5.500 -0.4452 0.01294 0.00841 -0.0299 1.0000 0.0036
-5.250 -0.4189 0.01191 0.00719 -0.0296 1.0000 0.0037
-5.000 -0.3923 0.01117 0.00632 -0.0293 1.0000 0.0038
-4.750 -0.3662 0.00989 0.00482 -0.0290 1.0000 0.0042
-4.500 -0.3394 0.00947 0.00436 -0.0287 1.0000 0.0046
-4.250 -0.3058 0.00907 0.00392 -0.0300 0.9868 0.0050
-4.000 -0.2689 0.00866 0.00343 -0.0319 0.9536 0.0054
-3.750 -0.2429 0.00851 0.00303 -0.0311 0.8710 0.0058
-3.500 -0.2196 0.00860 0.00267 -0.0298 0.7619 0.0060
-3.250 -0.1926 0.00849 0.00238 -0.0295 0.7294 0.0063
-3.000 -0.1651 0.00823 0.00201 -0.0294 0.7140 0.0075
-2.750 -0.1374 0.00807 0.00179 -0.0292 0.7033 0.0087
-2.500 -0.1095 0.00792 0.00158 -0.0291 0.6917 0.0100
-2.250 -0.0815 0.00774 0.00137 -0.0290 0.6782 0.0143
-2.000 -0.0536 0.00760 0.00121 -0.0289 0.6620 0.0215
-1.750 -0.0258 0.00748 0.00108 -0.0288 0.6431 0.0351
-1.500 0.0019 0.00730 0.00096 -0.0287 0.6234 0.0672
-1.250 0.0297 0.00716 0.00085 -0.0287 0.6025 0.1039
-1.000 0.0573 0.00701 0.00077 -0.0286 0.5817 0.1531
-0.750 0.0851 0.00686 0.00072 -0.0286 0.5614 0.2067
-0.500 0.1127 0.00669 0.00068 -0.0286 0.5406 0.2776
-0.250 0.1403 0.00651 0.00064 -0.0286 0.5198 0.3538
0.000 0.1678 0.00632 0.00063 -0.0287 0.4977 0.4461
0.250 0.1951 0.00606 0.00063 -0.0287 0.4742 0.5627
0.500 0.2219 0.00580 0.00064 -0.0285 0.4488 0.6880
0.750 0.2472 0.00555 0.00068 -0.0279 0.4236 0.8103
1.000 0.2700 0.00539 0.00072 -0.0265 0.3994 0.9041
1.250 0.3023 0.00541 0.00074 -0.0272 0.3713 0.9975
1.500 0.3302 0.00556 0.00078 -0.0272 0.3462 1.0000
1.750 0.3579 0.00573 0.00084 -0.0271 0.3199 1.0000
2.000 0.3857 0.00589 0.00090 -0.0270 0.2983 1.0000
2.250 0.4133 0.00608 0.00097 -0.0270 0.2722 1.0000
2.500 0.4409 0.00627 0.00106 -0.0269 0.2488 1.0000
2.750 0.4685 0.00647 0.00117 -0.0269 0.2247 1.0000
3.000 0.4960 0.00668 0.00128 -0.0268 0.2023 1.0000
3.250 0.5236 0.00688 0.00139 -0.0267 0.1831 1.0000
3.500 0.5510 0.00711 0.00153 -0.0266 0.1614 1.0000
3.750 0.5785 0.00731 0.00169 -0.0266 0.1455 1.0000
4.000 0.6059 0.00756 0.00185 -0.0265 0.1272 1.0000
4.250 0.6333 0.00777 0.00201 -0.0264 0.1145 1.0000
4.500 0.6607 0.00799 0.00219 -0.0263 0.1022 1.0000
4.750 0.6879 0.00823 0.00239 -0.0262 0.0900 1.0000
5.000 0.7152 0.00846 0.00259 -0.0261 0.0806 1.0000
5.250 0.7423 0.00872 0.00282 -0.0260 0.0696 1.0000
5.750 0.7963 0.00928 0.00332 -0.0258 0.0510 1.0000
6.000 0.8233 0.00955 0.00359 -0.0257 0.0441 1.0000
6.250 0.8500 0.00989 0.00389 -0.0256 0.0359 1.0000
6.500 0.8767 0.01020 0.00420 -0.0254 0.0304 1.0000
6.750 0.9032 0.01054 0.00453 -0.0253 0.0250 1.0000
7.000 0.9296 0.01092 0.00491 -0.0251 0.0202 1.0000
7.250 0.9560 0.01127 0.00529 -0.0249 0.0172 1.0000
7.500 0.9821 0.01167 0.00570 -0.0248 0.0144 1.0000
7.750 1.0081 0.01209 0.00614 -0.0246 0.0116 1.0000
8.000 1.0341 0.01250 0.00659 -0.0244 0.0101 1.0000
8.250 1.0596 0.01299 0.00710 -0.0241 0.0085 1.0000
8.500 1.0850 0.01349 0.00768 -0.0238 0.0074 1.0000
8.750 1.1105 0.01395 0.00821 -0.0236 0.0068 1.0000
9.000 1.1356 0.01446 0.00878 -0.0233 0.0061 1.0000
9.250 1.1603 0.01505 0.00941 -0.0230 0.0054 1.0000
9.500 1.1842 0.01581 0.01026 -0.0227 0.0046 1.0000
9.750 1.2088 0.01634 0.01087 -0.0224 0.0044 1.0000
10.000 1.2328 0.01697 0.01159 -0.0220 0.0041 1.0000
10.250 1.2564 0.01764 0.01237 -0.0216 0.0038 1.0000
10.500 1.2796 0.01836 0.01318 -0.0213 0.0035 1.0000
10.750 1.3022 0.01915 0.01406 -0.0208 0.0032 1.0000
11.000 1.3239 0.02007 0.01508 -0.0203 0.0030 1.0000
11.250 1.3435 0.02135 0.01652 -0.0197 0.0027 1.0000
11.500 1.3632 0.02251 0.01782 -0.0191 0.0026 1.0000
11.750 1.3831 0.02353 0.01897 -0.0185 0.0025 1.0000
12.000 1.4021 0.02465 0.02022 -0.0178 0.0024 1.0000
12.250 1.4197 0.02588 0.02160 -0.0171 0.0023 1.0000
12.500 1.4361 0.02719 0.02308 -0.0164 0.0022 1.0000
12.750 1.4511 0.02859 0.02463 -0.0156 0.0021 1.0000
13.000 1.4647 0.03005 0.02623 -0.0148 0.0020 1.0000
13.250 1.4760 0.03164 0.02796 -0.0139 0.0019 1.0000
13.500 1.4850 0.03333 0.02979 -0.0129 0.0018 1.0000
13.750 1.4872 0.03530 0.03190 -0.0115 0.0018 1.0000
14.000 1.4827 0.03786 0.03461 -0.0106 0.0017 1.0000
14.250 1.4748 0.04178 0.03870 -0.0124 0.0017 1.0000
14.500 1.4632 0.04764 0.04474 -0.0169 0.0017 1.0000
14.750 1.4419 0.05601 0.05332 -0.0234 0.0017 1.0000
15.000 1.4091 0.06704 0.06457 -0.0311 0.0017 1.0000
15.250 1.3500 0.08331 0.08108 -0.0408 0.0019 1.0000
15.500 1.2839 0.10065 0.09859 -0.0497 0.0020 1.0000
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Polar data table (+)
Polar graphs
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