AG45ct -02f (ag45ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG45ct -02f (ag45ct02r-il) Reynolds number: 200,000 Max Cl/Cd: 59.35 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag45ct02r-il-200000-n5.txt Download as CSV file: xf-ag45ct02r-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4682 0.07183 0.06869 -0.0004 1.0000 0.0130
-7.250 -0.5470 0.07486 0.07158 -0.0027 1.0000 0.0128
-7.000 -0.5364 0.06951 0.06621 -0.0082 1.0000 0.0124
-6.750 -0.5231 0.06353 0.06018 -0.0142 1.0000 0.0121
-6.500 -0.5075 0.05708 0.05360 -0.0199 1.0000 0.0117
-6.250 -0.4898 0.05026 0.04659 -0.0248 1.0000 0.0114
-6.000 -0.4707 0.04320 0.03922 -0.0285 1.0000 0.0111
-5.750 -0.4503 0.03652 0.03211 -0.0308 1.0000 0.0109
-5.500 -0.4286 0.03080 0.02585 -0.0318 1.0000 0.0110
-5.250 -0.4047 0.02692 0.02142 -0.0320 1.0000 0.0123
-5.000 -0.3793 0.02412 0.01804 -0.0317 1.0000 0.0131
-4.750 -0.3543 0.02157 0.01500 -0.0314 1.0000 0.0132
-4.500 -0.3286 0.01954 0.01258 -0.0309 1.0000 0.0133
-4.250 -0.3030 0.01755 0.01031 -0.0305 1.0000 0.0136
-4.000 -0.2774 0.01591 0.00849 -0.0300 1.0000 0.0141
-3.750 -0.2517 0.01480 0.00729 -0.0295 1.0000 0.0149
-3.500 -0.2258 0.01392 0.00635 -0.0291 1.0000 0.0161
-3.250 -0.1998 0.01315 0.00549 -0.0286 1.0000 0.0178
-3.000 -0.1739 0.01248 0.00477 -0.0282 1.0000 0.0218
-2.750 -0.1478 0.01191 0.00417 -0.0278 1.0000 0.0266
-2.500 -0.1140 0.01132 0.00356 -0.0290 0.9873 0.0399
-2.250 -0.0764 0.01065 0.00308 -0.0312 0.9588 0.0848
-2.000 -0.0392 0.01003 0.00279 -0.0334 0.9183 0.1761
-1.750 -0.0057 0.00944 0.00256 -0.0345 0.8683 0.2989
-1.500 0.0206 0.00889 0.00239 -0.0341 0.8219 0.4482
-1.250 0.0431 0.00840 0.00229 -0.0326 0.7872 0.6078
-1.000 0.0630 0.00795 0.00224 -0.0302 0.7614 0.7624
-0.750 0.0984 0.00768 0.00214 -0.0305 0.7400 0.9574
-0.500 0.1318 0.00778 0.00201 -0.0315 0.7213 1.0000
-0.250 0.1584 0.00793 0.00195 -0.0310 0.7058 1.0000
0.000 0.1854 0.00803 0.00191 -0.0307 0.6892 1.0000
0.250 0.2125 0.00812 0.00189 -0.0304 0.6717 1.0000
0.500 0.2396 0.00822 0.00186 -0.0301 0.6534 1.0000
0.750 0.2665 0.00833 0.00184 -0.0298 0.6344 1.0000
1.000 0.2936 0.00843 0.00183 -0.0294 0.6135 1.0000
1.250 0.3204 0.00856 0.00183 -0.0291 0.5920 1.0000
1.500 0.3473 0.00869 0.00186 -0.0288 0.5689 1.0000
1.750 0.3742 0.00884 0.00189 -0.0284 0.5452 1.0000
2.000 0.4009 0.00902 0.00194 -0.0281 0.5209 1.0000
2.250 0.4277 0.00920 0.00201 -0.0278 0.4959 1.0000
2.500 0.4545 0.00940 0.00212 -0.0275 0.4705 1.0000
2.750 0.4813 0.00961 0.00223 -0.0273 0.4454 1.0000
3.000 0.5080 0.00984 0.00236 -0.0270 0.4207 1.0000
3.250 0.5347 0.01009 0.00251 -0.0267 0.3962 1.0000
3.500 0.5614 0.01034 0.00272 -0.0265 0.3713 1.0000
3.750 0.5881 0.01061 0.00292 -0.0263 0.3478 1.0000
4.000 0.6146 0.01090 0.00313 -0.0261 0.3247 1.0000
4.250 0.6412 0.01120 0.00338 -0.0259 0.3017 1.0000
4.500 0.6677 0.01151 0.00367 -0.0257 0.2792 1.0000
4.750 0.6940 0.01186 0.00396 -0.0255 0.2564 1.0000
5.000 0.7203 0.01221 0.00428 -0.0252 0.2334 1.0000
5.250 0.7465 0.01259 0.00463 -0.0250 0.2110 1.0000
5.500 0.7724 0.01302 0.00503 -0.0248 0.1889 1.0000
5.750 0.7983 0.01345 0.00544 -0.0246 0.1674 1.0000
6.250 0.8494 0.01444 0.00639 -0.0241 0.1283 1.0000
6.500 0.8746 0.01499 0.00692 -0.0239 0.1102 1.0000
6.750 0.8995 0.01559 0.00753 -0.0236 0.0939 1.0000
7.000 0.9244 0.01619 0.00815 -0.0233 0.0785 1.0000
7.250 0.9490 0.01686 0.00884 -0.0230 0.0648 1.0000
7.500 0.9731 0.01759 0.00960 -0.0227 0.0524 1.0000
7.750 0.9967 0.01843 0.01047 -0.0223 0.0426 1.0000
8.000 1.0195 0.01939 0.01149 -0.0218 0.0343 1.0000
8.250 1.0428 0.02024 0.01249 -0.0214 0.0287 1.0000
8.500 1.0637 0.02151 0.01384 -0.0208 0.0245 1.0000
8.750 1.0859 0.02247 0.01497 -0.0202 0.0211 1.0000
9.000 1.1063 0.02369 0.01630 -0.0196 0.0183 1.0000
9.250 1.1241 0.02537 0.01815 -0.0188 0.0167 1.0000
9.500 1.1426 0.02685 0.01986 -0.0179 0.0154 1.0000
9.750 1.1605 0.02832 0.02151 -0.0171 0.0140 1.0000
10.000 1.1780 0.02967 0.02305 -0.0165 0.0126 1.0000
10.250 1.1890 0.03193 0.02546 -0.0155 0.0115 1.0000
10.500 1.2012 0.03402 0.02779 -0.0145 0.0110 1.0000
10.750 1.2110 0.03629 0.03035 -0.0134 0.0106 1.0000
11.000 1.2171 0.03885 0.03319 -0.0123 0.0101 1.0000
11.250 1.2183 0.04160 0.03622 -0.0111 0.0098 1.0000
11.500 1.2139 0.04462 0.03949 -0.0101 0.0096 1.0000
11.750 1.2066 0.04829 0.04342 -0.0106 0.0094 1.0000
12.000 1.1974 0.05284 0.04821 -0.0127 0.0093 1.0000
12.250 1.1862 0.05820 0.05380 -0.0159 0.0092 1.0000
12.500 1.1726 0.06444 0.06026 -0.0200 0.0092 1.0000
12.750 1.1566 0.07155 0.06759 -0.0249 0.0092 1.0000
13.000 1.1383 0.07951 0.07573 -0.0302 0.0092 1.0000
13.250 1.1176 0.08826 0.08465 -0.0359 0.0094 1.0000
13.500 1.0949 0.09777 0.09430 -0.0417 0.0095 1.0000
13.750 1.0704 0.10797 0.10463 -0.0477 0.0097 1.0000
14.000 1.0429 0.11942 0.11617 -0.0541 0.0100 1.0000
14.250 1.0131 0.13231 0.12913 -0.0609 0.0104 1.0000
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Polar data table (+)
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