AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG455ct -02f rot. (ag455ct02r-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.6 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag455ct02r-il-1000000-n5.txt Download as CSV file: xf-ag455ct02r-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG455ct -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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4781 0.11369 0.11217 0.0179 1.0000 0.0058
-10.000 -0.4770 0.10971 0.10820 0.0169 1.0000 0.0058
-9.500 -0.6016 0.11350 0.11191 0.0301 1.0000 0.0058
-9.250 -0.5978 0.10950 0.10792 0.0283 1.0000 0.0058
-9.000 -0.5940 0.10549 0.10392 0.0265 1.0000 0.0058
-8.500 -0.5871 0.09736 0.09582 0.0225 1.0000 0.0058
-6.500 -0.5360 0.01904 0.01554 -0.0322 1.0000 0.0033
-6.250 -0.5120 0.01615 0.01217 -0.0321 1.0000 0.0034
-6.000 -0.4863 0.01464 0.01039 -0.0319 1.0000 0.0035
-5.750 -0.4613 0.01243 0.00777 -0.0317 1.0000 0.0038
-5.500 -0.4348 0.01167 0.00691 -0.0315 1.0000 0.0040
-5.250 -0.4080 0.01117 0.00634 -0.0312 1.0000 0.0043
-5.000 -0.3812 0.01068 0.00578 -0.0310 1.0000 0.0045
-4.750 -0.3470 0.01011 0.00512 -0.0324 0.9822 0.0048
-4.500 -0.3111 0.00961 0.00449 -0.0340 0.9358 0.0051
-4.250 -0.2884 0.00946 0.00398 -0.0325 0.8367 0.0053
-4.000 -0.2636 0.00936 0.00352 -0.0317 0.7561 0.0055
-3.750 -0.2365 0.00917 0.00317 -0.0315 0.7297 0.0057
-3.500 -0.2089 0.00891 0.00279 -0.0313 0.7154 0.0061
-3.250 -0.1813 0.00857 0.00234 -0.0312 0.7060 0.0067
-3.000 -0.1533 0.00833 0.00204 -0.0310 0.6967 0.0073
-2.750 -0.1253 0.00814 0.00180 -0.0309 0.6856 0.0083
-2.500 -0.0973 0.00796 0.00157 -0.0308 0.6724 0.0103
-2.250 -0.0693 0.00782 0.00138 -0.0307 0.6573 0.0141
-2.000 -0.0413 0.00769 0.00123 -0.0306 0.6405 0.0215
-1.750 -0.0135 0.00755 0.00109 -0.0305 0.6226 0.0380
-1.500 0.0144 0.00737 0.00098 -0.0305 0.6032 0.0712
-1.250 0.0422 0.00724 0.00087 -0.0305 0.5829 0.1060
-1.000 0.0700 0.00708 0.00080 -0.0305 0.5625 0.1577
-0.750 0.0978 0.00695 0.00074 -0.0305 0.5412 0.2082
-0.500 0.1256 0.00679 0.00070 -0.0305 0.5201 0.2747
-0.250 0.1533 0.00664 0.00067 -0.0305 0.4980 0.3462
0.000 0.1810 0.00647 0.00066 -0.0305 0.4767 0.4305
0.250 0.2084 0.00624 0.00066 -0.0306 0.4545 0.5415
0.500 0.2355 0.00599 0.00068 -0.0305 0.4329 0.6588
0.750 0.2618 0.00577 0.00072 -0.0301 0.4108 0.7717
1.000 0.2858 0.00557 0.00077 -0.0290 0.3896 0.8751
1.250 0.3134 0.00548 0.00079 -0.0286 0.3684 0.9795
1.500 0.3436 0.00562 0.00082 -0.0291 0.3458 1.0000
1.750 0.3715 0.00577 0.00087 -0.0290 0.3254 1.0000
2.000 0.3993 0.00592 0.00093 -0.0290 0.3051 1.0000
2.250 0.4271 0.00608 0.00100 -0.0289 0.2854 1.0000
2.500 0.4549 0.00624 0.00109 -0.0289 0.2662 1.0000
2.750 0.4827 0.00642 0.00117 -0.0288 0.2467 1.0000
3.000 0.5104 0.00660 0.00127 -0.0288 0.2285 1.0000
3.250 0.5381 0.00678 0.00138 -0.0287 0.2105 1.0000
3.500 0.5657 0.00699 0.00152 -0.0287 0.1918 1.0000
4.000 0.6208 0.00740 0.00180 -0.0286 0.1589 1.0000
4.250 0.6483 0.00761 0.00195 -0.0285 0.1450 1.0000
4.500 0.6757 0.00785 0.00214 -0.0284 0.1286 1.0000
4.750 0.7030 0.00808 0.00232 -0.0284 0.1163 1.0000
5.000 0.7303 0.00834 0.00253 -0.0283 0.1021 1.0000
5.250 0.7575 0.00859 0.00274 -0.0282 0.0911 1.0000
5.500 0.7846 0.00887 0.00298 -0.0281 0.0788 1.0000
5.750 0.8116 0.00916 0.00323 -0.0280 0.0683 1.0000
6.000 0.8385 0.00947 0.00351 -0.0279 0.0573 1.0000
6.250 0.8652 0.00980 0.00380 -0.0278 0.0477 1.0000
6.500 0.8920 0.01012 0.00410 -0.0277 0.0398 1.0000
6.750 0.9186 0.01046 0.00444 -0.0276 0.0333 1.0000
7.000 0.9449 0.01085 0.00481 -0.0274 0.0259 1.0000
7.250 0.9714 0.01120 0.00517 -0.0273 0.0221 1.0000
7.500 0.9975 0.01161 0.00557 -0.0271 0.0176 1.0000
7.750 1.0237 0.01199 0.00598 -0.0269 0.0151 1.0000
8.000 1.0494 0.01246 0.00647 -0.0267 0.0117 1.0000
8.250 1.0753 0.01286 0.00691 -0.0265 0.0104 1.0000
8.500 1.1008 0.01334 0.00742 -0.0263 0.0089 1.0000
8.750 1.1259 0.01389 0.00802 -0.0260 0.0075 1.0000
9.000 1.1513 0.01434 0.00853 -0.0258 0.0069 1.0000
9.250 1.1763 0.01485 0.00910 -0.0255 0.0061 1.0000
9.500 1.2008 0.01545 0.00974 -0.0252 0.0053 1.0000
9.750 1.2246 0.01617 0.01056 -0.0248 0.0046 1.0000
10.000 1.2489 0.01674 0.01121 -0.0245 0.0044 1.0000
10.250 1.2727 0.01737 0.01193 -0.0242 0.0041 1.0000
10.500 1.2961 0.01805 0.01270 -0.0238 0.0038 1.0000
10.750 1.3190 0.01878 0.01351 -0.0234 0.0035 1.0000
11.000 1.3412 0.01959 0.01440 -0.0229 0.0032 1.0000
11.250 1.3622 0.02056 0.01548 -0.0224 0.0029 1.0000
11.500 1.3808 0.02191 0.01698 -0.0217 0.0027 1.0000
11.750 1.4012 0.02283 0.01804 -0.0211 0.0026 1.0000
12.000 1.4210 0.02378 0.01911 -0.0205 0.0025 1.0000
12.250 1.4397 0.02482 0.02027 -0.0199 0.0024 1.0000
12.500 1.4575 0.02593 0.02150 -0.0192 0.0023 1.0000
12.750 1.4739 0.02711 0.02280 -0.0184 0.0021 1.0000
13.000 1.4889 0.02838 0.02419 -0.0176 0.0020 1.0000
13.250 1.5020 0.02977 0.02571 -0.0167 0.0019 1.0000
13.500 1.5124 0.03132 0.02739 -0.0157 0.0018 1.0000
13.750 1.5176 0.03311 0.02931 -0.0144 0.0017 1.0000
14.000 1.5155 0.03527 0.03162 -0.0129 0.0017 1.0000
14.250 1.5092 0.03842 0.03493 -0.0131 0.0017 1.0000
14.500 1.5008 0.04308 0.03978 -0.0160 0.0016 1.0000
14.750 1.4886 0.04903 0.04591 -0.0202 0.0016 1.0000
15.000 1.4704 0.05650 0.05356 -0.0254 0.0016 1.0000
15.250 1.4433 0.06586 0.06309 -0.0315 0.0016 1.0000
15.500 1.4080 0.07678 0.07419 -0.0378 0.0017 1.0000
15.750 1.3641 0.08925 0.08683 -0.0444 0.0017 1.0000
16.000 1.3155 0.10268 0.10042 -0.0511 0.0018 1.0000
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Polar data table (+)
Polar graphs
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