AG45ct -02f (ag45ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG45ct -02f (ag45ct02r-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.56 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag45ct02r-il-1000000.txt Download as CSV file: xf-ag45ct02r-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5719 0.09311 0.09160 0.0172 1.0000 0.0088
-8.000 -0.5687 0.08890 0.08740 0.0146 1.0000 0.0088
-7.750 -0.5656 0.08454 0.08306 0.0114 1.0000 0.0088
-7.500 -0.5590 0.07951 0.07805 0.0060 1.0000 0.0088
-7.250 -0.5476 0.07367 0.07219 -0.0011 1.0000 0.0088
-7.000 -0.5331 0.06726 0.06576 -0.0087 1.0000 0.0089
-6.750 -0.5163 0.06044 0.05888 -0.0157 1.0000 0.0089
-6.500 -0.4979 0.05339 0.05172 -0.0216 1.0000 0.0089
-6.250 -0.4875 0.03991 0.03787 -0.0292 1.0000 0.0092
-6.000 -0.4693 0.03473 0.03244 -0.0312 1.0000 0.0095
-5.750 -0.4481 0.03161 0.02914 -0.0320 1.0000 0.0098
-5.500 -0.4259 0.02849 0.02580 -0.0326 1.0000 0.0101
-5.250 -0.4028 0.02541 0.02246 -0.0327 1.0000 0.0106
-5.000 -0.3811 0.01577 0.01170 -0.0314 1.0000 0.0074
-4.750 -0.3558 0.01332 0.00886 -0.0307 1.0000 0.0076
-4.500 -0.3298 0.01226 0.00763 -0.0302 1.0000 0.0082
-4.250 -0.3038 0.01147 0.00673 -0.0296 1.0000 0.0085
-4.000 -0.2778 0.01085 0.00602 -0.0291 1.0000 0.0087
-3.750 -0.2462 0.01008 0.00516 -0.0298 0.9963 0.0089
-3.500 -0.2093 0.00866 0.00358 -0.0318 0.9829 0.0097
-3.250 -0.1721 0.00809 0.00293 -0.0337 0.9502 0.0104
-3.000 -0.1465 0.00787 0.00245 -0.0326 0.8687 0.0110
-2.750 -0.1222 0.00782 0.00207 -0.0315 0.7946 0.0123
-2.500 -0.0955 0.00759 0.00165 -0.0310 0.7591 0.0171
-2.250 -0.0682 0.00737 0.00139 -0.0308 0.7392 0.0352
-2.000 -0.0408 0.00716 0.00124 -0.0306 0.7247 0.0695
-1.750 -0.0134 0.00690 0.00113 -0.0306 0.7132 0.1293
-1.500 0.0139 0.00664 0.00105 -0.0305 0.7036 0.2027
-1.250 0.0415 0.00630 0.00097 -0.0305 0.6924 0.2915
-1.000 0.0687 0.00589 0.00091 -0.0305 0.6806 0.4141
-0.750 0.0954 0.00544 0.00087 -0.0304 0.6674 0.5592
-0.500 0.1217 0.00506 0.00084 -0.0301 0.6526 0.6884
-0.250 0.1458 0.00466 0.00083 -0.0290 0.6362 0.8256
0.000 0.1724 0.00438 0.00082 -0.0281 0.6181 0.9696
0.250 0.2088 0.00445 0.00077 -0.0299 0.5962 1.0000
0.500 0.2364 0.00454 0.00076 -0.0298 0.5751 1.0000
0.750 0.2640 0.00465 0.00075 -0.0296 0.5524 1.0000
1.000 0.2916 0.00476 0.00076 -0.0294 0.5295 1.0000
1.250 0.3192 0.00489 0.00078 -0.0293 0.5063 1.0000
1.500 0.3468 0.00502 0.00081 -0.0292 0.4827 1.0000
1.750 0.3744 0.00516 0.00084 -0.0290 0.4594 1.0000
2.000 0.4020 0.00531 0.00089 -0.0289 0.4355 1.0000
2.250 0.4295 0.00547 0.00095 -0.0288 0.4112 1.0000
2.500 0.4571 0.00562 0.00102 -0.0287 0.3886 1.0000
2.750 0.4846 0.00580 0.00110 -0.0286 0.3655 1.0000
3.000 0.5122 0.00597 0.00119 -0.0285 0.3441 1.0000
3.250 0.5396 0.00615 0.00129 -0.0284 0.3222 1.0000
3.500 0.5671 0.00634 0.00141 -0.0283 0.3016 1.0000
3.750 0.5945 0.00654 0.00153 -0.0282 0.2803 1.0000
4.000 0.6219 0.00673 0.00166 -0.0281 0.2607 1.0000
4.250 0.6491 0.00696 0.00181 -0.0280 0.2390 1.0000
4.500 0.6764 0.00719 0.00198 -0.0279 0.2183 1.0000
4.750 0.7034 0.00745 0.00215 -0.0278 0.1963 1.0000
5.000 0.7304 0.00773 0.00235 -0.0277 0.1753 1.0000
5.250 0.7574 0.00801 0.00256 -0.0276 0.1553 1.0000
5.500 0.7841 0.00833 0.00280 -0.0275 0.1357 1.0000
5.750 0.8109 0.00863 0.00305 -0.0274 0.1189 1.0000
6.000 0.8376 0.00895 0.00331 -0.0272 0.1028 1.0000
6.250 0.8641 0.00930 0.00360 -0.0271 0.0869 1.0000
6.500 0.8904 0.00967 0.00391 -0.0269 0.0723 1.0000
6.750 0.9166 0.01006 0.00426 -0.0267 0.0590 1.0000
7.000 0.9426 0.01049 0.00463 -0.0266 0.0463 1.0000
7.250 0.9686 0.01092 0.00503 -0.0264 0.0364 1.0000
7.500 0.9944 0.01136 0.00545 -0.0261 0.0289 1.0000
7.750 1.0201 0.01182 0.00593 -0.0259 0.0227 1.0000
8.000 1.0451 0.01245 0.00657 -0.0255 0.0170 1.0000
8.250 1.0708 0.01287 0.00703 -0.0253 0.0146 1.0000
8.500 1.0944 0.01379 0.00802 -0.0248 0.0114 1.0000
8.750 1.1199 0.01421 0.00850 -0.0245 0.0106 1.0000
9.000 1.1448 0.01472 0.00906 -0.0242 0.0094 1.0000
9.250 1.1682 0.01552 0.00992 -0.0238 0.0080 1.0000
9.500 1.1901 0.01663 0.01120 -0.0232 0.0072 1.0000
9.750 1.2140 0.01725 0.01190 -0.0228 0.0068 1.0000
10.000 1.2371 0.01799 0.01273 -0.0223 0.0063 1.0000
10.250 1.2596 0.01878 0.01361 -0.0219 0.0058 1.0000
10.500 1.2814 0.01966 0.01457 -0.0214 0.0054 1.0000
10.750 1.2999 0.02105 0.01609 -0.0206 0.0050 1.0000
11.000 1.3076 0.02405 0.01942 -0.0189 0.0046 1.0000
11.250 1.3275 0.02496 0.02044 -0.0183 0.0045 1.0000
11.500 1.3451 0.02612 0.02173 -0.0175 0.0043 1.0000
11.750 1.3605 0.02749 0.02327 -0.0167 0.0041 1.0000
12.000 1.3742 0.02895 0.02486 -0.0157 0.0039 1.0000
12.250 1.3863 0.03046 0.02651 -0.0148 0.0037 1.0000
12.500 1.3961 0.03206 0.02824 -0.0138 0.0036 1.0000
12.750 1.4006 0.03373 0.03004 -0.0124 0.0034 1.0000
13.000 1.3998 0.03596 0.03239 -0.0115 0.0033 1.0000
13.250 1.3968 0.03907 0.03565 -0.0123 0.0033 1.0000
13.500 1.3911 0.04344 0.04019 -0.0151 0.0032 1.0000
13.750 1.3818 0.04880 0.04571 -0.0186 0.0032 1.0000
14.000 1.3688 0.05515 0.05222 -0.0228 0.0032 1.0000
14.250 1.3510 0.06256 0.05980 -0.0275 0.0032 1.0000
14.500 1.3288 0.07088 0.06828 -0.0324 0.0032 1.0000
14.750 1.3038 0.07972 0.07727 -0.0373 0.0032 1.0000
15.000 1.2749 0.08931 0.08700 -0.0423 0.0033 1.0000
15.250 1.2429 0.09962 0.09746 -0.0475 0.0034 1.0000
15.500 1.2110 0.11028 0.10826 -0.0528 0.0034 1.0000
15.750 1.1793 0.12146 0.11956 -0.0584 0.0036 1.0000
16.000 1.1472 0.13333 0.13156 -0.0644 0.0037 1.0000
16.250 1.1170 0.14543 0.14378 -0.0705 0.0038 1.0000
16.500 1.0794 0.16061 0.15906 -0.0783 0.0041 1.0000
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Polar data table (+)
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