AG46ct -02f rot. (ag46ct02r-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG46ct -02f rot. (ag46ct02r-il) Reynolds number: 500,000 Max Cl/Cd: 72.52 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag46ct02r-il-500000-n5.txt Download as CSV file: xf-ag46ct02r-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5865 0.09559 0.09343 0.0194 1.0000 0.0099
-8.000 -0.5829 0.09144 0.08930 0.0169 1.0000 0.0100
-7.750 -0.5793 0.08718 0.08506 0.0139 1.0000 0.0100
-6.250 -0.5056 0.04767 0.04517 -0.0226 1.0000 0.0061
-6.000 -0.4848 0.04054 0.03778 -0.0265 1.0000 0.0059
-5.750 -0.4630 0.03292 0.02976 -0.0290 1.0000 0.0057
-5.500 -0.4410 0.02449 0.02063 -0.0301 1.0000 0.0055
-5.250 -0.4171 0.01876 0.01411 -0.0301 1.0000 0.0054
-5.000 -0.3914 0.01595 0.01076 -0.0297 1.0000 0.0056
-4.750 -0.3651 0.01425 0.00873 -0.0293 1.0000 0.0059
-4.500 -0.3386 0.01316 0.00742 -0.0289 1.0000 0.0063
-4.250 -0.3125 0.01191 0.00598 -0.0286 1.0000 0.0067
-4.000 -0.2860 0.01121 0.00522 -0.0283 1.0000 0.0072
-3.750 -0.2594 0.01073 0.00469 -0.0280 1.0000 0.0079
-3.500 -0.2328 0.01036 0.00429 -0.0277 1.0000 0.0089
-3.250 -0.2061 0.00991 0.00378 -0.0273 0.9998 0.0097
-3.000 -0.1706 0.00926 0.00304 -0.0289 0.9842 0.0105
-2.750 -0.1333 0.00878 0.00251 -0.0308 0.9544 0.0127
-2.500 -0.0992 0.00854 0.00209 -0.0318 0.8840 0.0161
-2.250 -0.0759 0.00857 0.00182 -0.0303 0.7926 0.0241
-1.750 -0.0236 0.00833 0.00146 -0.0294 0.7226 0.0809
-1.500 0.0035 0.00813 0.00134 -0.0293 0.7072 0.1332
-1.250 0.0308 0.00788 0.00124 -0.0292 0.6925 0.2008
-1.000 0.0583 0.00761 0.00117 -0.0292 0.6760 0.2796
-0.750 0.0854 0.00724 0.00110 -0.0292 0.6575 0.3940
-0.500 0.1118 0.00679 0.00105 -0.0290 0.6375 0.5421
-0.250 0.1369 0.00631 0.00102 -0.0284 0.6165 0.7059
0.000 0.1590 0.00595 0.00103 -0.0268 0.5955 0.8439
0.250 0.1869 0.00579 0.00099 -0.0262 0.5726 0.9626
0.500 0.2199 0.00589 0.00095 -0.0272 0.5482 1.0000
0.750 0.2474 0.00602 0.00094 -0.0270 0.5247 1.0000
1.000 0.2750 0.00615 0.00095 -0.0269 0.4994 1.0000
1.250 0.3025 0.00630 0.00097 -0.0267 0.4728 1.0000
1.500 0.3300 0.00646 0.00101 -0.0266 0.4457 1.0000
1.750 0.3574 0.00664 0.00105 -0.0265 0.4169 1.0000
2.000 0.3848 0.00683 0.00111 -0.0264 0.3885 1.0000
2.250 0.4122 0.00703 0.00119 -0.0263 0.3598 1.0000
2.500 0.4396 0.00723 0.00128 -0.0262 0.3329 1.0000
2.750 0.4670 0.00746 0.00141 -0.0261 0.3045 1.0000
3.000 0.4942 0.00770 0.00153 -0.0260 0.2766 1.0000
3.250 0.5215 0.00795 0.00168 -0.0259 0.2492 1.0000
3.500 0.5487 0.00822 0.00184 -0.0258 0.2224 1.0000
3.750 0.5759 0.00848 0.00203 -0.0257 0.1997 1.0000
4.000 0.6029 0.00877 0.00223 -0.0256 0.1754 1.0000
4.250 0.6300 0.00905 0.00244 -0.0255 0.1559 1.0000
4.500 0.6570 0.00936 0.00267 -0.0254 0.1365 1.0000
4.750 0.6840 0.00964 0.00293 -0.0253 0.1213 1.0000
5.000 0.7109 0.00994 0.00319 -0.0251 0.1074 1.0000
5.250 0.7378 0.01025 0.00347 -0.0250 0.0939 1.0000
5.500 0.7645 0.01057 0.00377 -0.0249 0.0827 1.0000
5.750 0.7911 0.01092 0.00411 -0.0247 0.0711 1.0000
6.000 0.8177 0.01128 0.00445 -0.0246 0.0610 1.0000
6.250 0.8441 0.01164 0.00482 -0.0244 0.0518 1.0000
6.500 0.8705 0.01203 0.00522 -0.0242 0.0440 1.0000
6.750 0.8965 0.01248 0.00566 -0.0241 0.0361 1.0000
7.000 0.9225 0.01291 0.00613 -0.0239 0.0301 1.0000
7.250 0.9483 0.01339 0.00665 -0.0236 0.0252 1.0000
7.500 0.9739 0.01391 0.00718 -0.0234 0.0206 1.0000
7.750 0.9992 0.01447 0.00780 -0.0231 0.0173 1.0000
8.000 1.0245 0.01501 0.00842 -0.0228 0.0149 1.0000
8.250 1.0489 0.01576 0.00922 -0.0225 0.0125 1.0000
8.500 1.0735 0.01640 0.01000 -0.0222 0.0111 1.0000
8.750 1.0980 0.01703 0.01071 -0.0218 0.0098 1.0000
9.000 1.1218 0.01779 0.01156 -0.0215 0.0086 1.0000
9.250 1.1436 0.01899 0.01290 -0.0209 0.0076 1.0000
9.500 1.1667 0.01983 0.01388 -0.0205 0.0072 1.0000
9.750 1.1889 0.02081 0.01501 -0.0200 0.0067 1.0000
10.000 1.2105 0.02182 0.01618 -0.0195 0.0062 1.0000
10.250 1.2320 0.02279 0.01726 -0.0190 0.0057 1.0000
10.500 1.2526 0.02384 0.01847 -0.0185 0.0052 1.0000
10.750 1.2679 0.02579 0.02061 -0.0177 0.0046 1.0000
11.000 1.2862 0.02708 0.02209 -0.0171 0.0045 1.0000
11.250 1.3022 0.02865 0.02387 -0.0163 0.0043 1.0000
11.500 1.3160 0.03042 0.02586 -0.0155 0.0041 1.0000
11.750 1.3273 0.03239 0.02805 -0.0146 0.0039 1.0000
12.000 1.3355 0.03456 0.03044 -0.0137 0.0037 1.0000
12.250 1.3396 0.03698 0.03307 -0.0129 0.0036 1.0000
12.500 1.3360 0.03964 0.03594 -0.0118 0.0035 1.0000
12.750 1.3276 0.04340 0.03991 -0.0129 0.0035 1.0000
13.000 1.3173 0.04894 0.04566 -0.0172 0.0034 1.0000
13.250 1.3026 0.05615 0.05309 -0.0230 0.0034 1.0000
13.500 1.2826 0.06488 0.06201 -0.0295 0.0035 1.0000
13.750 1.2556 0.07509 0.07240 -0.0363 0.0035 1.0000
14.000 1.2259 0.08573 0.08319 -0.0424 0.0036 1.0000
14.250 1.1946 0.09662 0.09419 -0.0482 0.0037 1.0000
14.500 1.1633 0.10756 0.10523 -0.0538 0.0038 1.0000
14.750 1.1329 0.11852 0.11628 -0.0592 0.0040 1.0000
15.000 1.1046 0.12954 0.12736 -0.0646 0.0041 1.0000
15.250 1.0781 0.14084 0.13873 -0.0702 0.0042 1.0000
15.500 1.0508 0.15307 0.15102 -0.0762 0.0043 1.0000
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Polar data table (+)
Polar graphs
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