AG45ct -02f (ag45ct02r-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG45ct -02f (ag45ct02r-il) Reynolds number: 500,000 Max Cl/Cd: 80.49 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag45ct02r-il-500000.txt Download as CSV file: xf-ag45ct02r-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5768 0.09664 0.09451 0.0157 1.0000 0.0137
-8.250 -0.5758 0.09248 0.09037 0.0140 1.0000 0.0139
-8.000 -0.5723 0.08884 0.08675 0.0122 1.0000 0.0142
-7.750 -0.5682 0.08521 0.08314 0.0100 1.0000 0.0144
-7.500 -0.5618 0.08118 0.07913 0.0063 1.0000 0.0146
-7.250 -0.5518 0.07662 0.07457 0.0012 1.0000 0.0149
-7.000 -0.5394 0.07161 0.06956 -0.0046 1.0000 0.0152
-6.750 -0.5246 0.06624 0.06415 -0.0107 1.0000 0.0156
-6.500 -0.5076 0.06061 0.05845 -0.0166 1.0000 0.0161
-6.250 -0.4886 0.05481 0.05255 -0.0218 1.0000 0.0167
-6.000 -0.4677 0.04888 0.04644 -0.0262 1.0000 0.0176
-5.750 -0.4405 0.04328 0.04058 -0.0291 1.0000 0.0193
-5.500 -0.4153 0.03953 0.03648 -0.0303 1.0000 0.0198
-5.250 -0.3844 0.01672 0.01342 -0.0323 1.0000 0.0211
-5.000 -0.3645 0.01445 0.01105 -0.0324 1.0000 0.0219
-4.750 -0.3433 0.01246 0.00889 -0.0322 1.0000 0.0232
-4.500 -0.3288 0.01728 0.01214 -0.0311 1.0000 0.0139
-4.250 -0.3030 0.01548 0.01006 -0.0305 1.0000 0.0139
-4.000 -0.2776 0.01369 0.00809 -0.0300 1.0000 0.0146
-3.750 -0.2519 0.01301 0.00738 -0.0296 1.0000 0.0160
-3.500 -0.2259 0.01172 0.00593 -0.0289 1.0000 0.0159
-3.250 -0.2001 0.01072 0.00483 -0.0282 1.0000 0.0160
-3.000 -0.1742 0.00997 0.00402 -0.0276 1.0000 0.0168
-2.750 -0.1480 0.00939 0.00339 -0.0271 1.0000 0.0186
-2.500 -0.1077 0.00860 0.00255 -0.0297 0.9882 0.0255
-2.250 -0.0673 0.00791 0.00202 -0.0323 0.9651 0.0713
-2.000 -0.0302 0.00733 0.00178 -0.0343 0.9199 0.1732
-1.750 -0.0049 0.00699 0.00160 -0.0335 0.8541 0.2782
-1.500 0.0187 0.00658 0.00149 -0.0326 0.8052 0.4263
-1.250 0.0423 0.00608 0.00143 -0.0318 0.7743 0.6084
-1.000 0.0638 0.00557 0.00142 -0.0301 0.7527 0.7840
-0.750 0.0934 0.00525 0.00140 -0.0295 0.7350 0.9695
-0.500 0.1291 0.00535 0.00132 -0.0311 0.7188 1.0000
-0.250 0.1562 0.00547 0.00129 -0.0307 0.7052 1.0000
0.000 0.1836 0.00555 0.00127 -0.0305 0.6905 1.0000
0.250 0.2111 0.00561 0.00124 -0.0303 0.6750 1.0000
0.500 0.2386 0.00566 0.00121 -0.0301 0.6579 1.0000
0.750 0.2661 0.00573 0.00119 -0.0298 0.6392 1.0000
1.000 0.2934 0.00582 0.00117 -0.0296 0.6192 1.0000
1.250 0.3208 0.00592 0.00117 -0.0294 0.5970 1.0000
1.500 0.3481 0.00604 0.00118 -0.0291 0.5737 1.0000
1.750 0.3753 0.00618 0.00121 -0.0289 0.5495 1.0000
2.000 0.4026 0.00633 0.00125 -0.0287 0.5246 1.0000
2.250 0.4299 0.00648 0.00131 -0.0285 0.4994 1.0000
2.500 0.4571 0.00666 0.00139 -0.0283 0.4736 1.0000
2.750 0.4844 0.00685 0.00147 -0.0281 0.4478 1.0000
3.000 0.5115 0.00705 0.00157 -0.0280 0.4227 1.0000
3.250 0.5387 0.00726 0.00169 -0.0278 0.3970 1.0000
3.500 0.5659 0.00747 0.00184 -0.0277 0.3727 1.0000
3.750 0.5930 0.00770 0.00198 -0.0275 0.3481 1.0000
4.000 0.6200 0.00794 0.00214 -0.0274 0.3248 1.0000
4.250 0.6470 0.00820 0.00232 -0.0272 0.3006 1.0000
4.500 0.6740 0.00845 0.00253 -0.0271 0.2782 1.0000
4.750 0.7009 0.00874 0.00274 -0.0269 0.2541 1.0000
5.000 0.7276 0.00905 0.00297 -0.0268 0.2303 1.0000
5.250 0.7542 0.00937 0.00322 -0.0267 0.2058 1.0000
5.500 0.7808 0.00972 0.00352 -0.0265 0.1827 1.0000
5.750 0.8070 0.01011 0.00383 -0.0263 0.1598 1.0000
6.000 0.8333 0.01049 0.00416 -0.0262 0.1390 1.0000
6.250 0.8593 0.01093 0.00453 -0.0260 0.1196 1.0000
6.500 0.8854 0.01134 0.00491 -0.0258 0.1019 1.0000
6.750 0.9111 0.01183 0.00535 -0.0256 0.0845 1.0000
7.000 0.9365 0.01236 0.00583 -0.0253 0.0682 1.0000
7.250 0.9619 0.01290 0.00635 -0.0251 0.0543 1.0000
7.500 0.9868 0.01353 0.00697 -0.0248 0.0421 1.0000
7.750 1.0113 0.01426 0.00770 -0.0244 0.0326 1.0000
8.000 1.0343 0.01533 0.00881 -0.0238 0.0250 1.0000
8.250 1.0593 0.01588 0.00947 -0.0235 0.0218 1.0000
8.500 1.0808 0.01716 0.01082 -0.0228 0.0177 1.0000
8.750 1.1041 0.01799 0.01178 -0.0223 0.0160 1.0000
9.000 1.1268 0.01890 0.01280 -0.0217 0.0144 1.0000
9.250 1.1485 0.01993 0.01392 -0.0211 0.0130 1.0000
9.500 1.1632 0.02229 0.01648 -0.0199 0.0117 1.0000
9.750 1.1819 0.02379 0.01819 -0.0190 0.0110 1.0000
10.000 1.2029 0.02476 0.01929 -0.0184 0.0102 1.0000
10.250 1.2216 0.02603 0.02072 -0.0176 0.0094 1.0000
10.500 1.2383 0.02755 0.02239 -0.0168 0.0089 1.0000
10.750 1.2535 0.02916 0.02414 -0.0159 0.0084 1.0000
11.000 1.2648 0.03121 0.02637 -0.0148 0.0081 1.0000
11.250 1.2679 0.03430 0.02970 -0.0134 0.0077 1.0000
11.500 1.2602 0.03842 0.03415 -0.0116 0.0075 1.0000
11.750 1.2445 0.04255 0.03857 -0.0100 0.0074 1.0000
12.250 1.2144 0.05275 0.04926 -0.0139 0.0074 1.0000
12.500 1.2039 0.05819 0.05489 -0.0176 0.0073 1.0000
12.750 1.1874 0.06505 0.06195 -0.0222 0.0074 1.0000
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Polar data table (+)
Polar graphs
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