AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG455ct -02f rot. (ag455ct02r-il) Reynolds number: 500,000 Max Cl/Cd: 78.74 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag455ct02r-il-500000.txt Download as CSV file: xf-ag455ct02r-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5692 0.09723 0.09508 0.0172 1.0000 0.0139
-8.000 -0.5650 0.09311 0.09098 0.0145 1.0000 0.0139
-7.750 -0.5607 0.08886 0.08676 0.0113 1.0000 0.0139
-7.500 -0.5532 0.08406 0.08197 0.0064 1.0000 0.0140
-7.250 -0.5519 0.07567 0.07361 -0.0017 1.0000 0.0143
-7.000 -0.5421 0.07040 0.06832 -0.0066 1.0000 0.0147
-6.750 -0.5284 0.06594 0.06382 -0.0107 1.0000 0.0150
-6.500 -0.5123 0.06152 0.05935 -0.0147 1.0000 0.0153
-6.250 -0.4941 0.05687 0.05463 -0.0188 1.0000 0.0158
-4.250 -0.3004 0.01806 0.01304 -0.0313 1.0000 0.0142
-4.000 -0.2738 0.01609 0.01078 -0.0309 1.0000 0.0141
-3.750 -0.2475 0.01379 0.00817 -0.0304 1.0000 0.0143
-3.500 -0.2217 0.01215 0.00641 -0.0301 1.0000 0.0159
-3.250 -0.1951 0.01108 0.00523 -0.0296 1.0000 0.0161
-3.000 -0.1686 0.01019 0.00426 -0.0290 1.0000 0.0165
-2.750 -0.1420 0.00951 0.00354 -0.0286 1.0000 0.0177
-2.500 -0.1153 0.00900 0.00299 -0.0281 1.0000 0.0203
-2.250 -0.0883 0.00837 0.00231 -0.0278 1.0000 0.0287
-2.000 -0.0495 0.00767 0.00187 -0.0302 0.9884 0.0899
-1.750 -0.0087 0.00706 0.00168 -0.0333 0.9606 0.2065
-1.500 0.0264 0.00647 0.00152 -0.0348 0.9001 0.3575
-1.250 0.0486 0.00597 0.00139 -0.0335 0.8240 0.5515
-1.000 0.0681 0.00535 0.00139 -0.0313 0.7783 0.7887
-0.750 0.0915 0.00509 0.00136 -0.0293 0.7502 0.9628
-0.500 0.1262 0.00521 0.00128 -0.0306 0.7285 1.0000
-0.250 0.1534 0.00535 0.00124 -0.0303 0.7112 1.0000
0.000 0.1809 0.00546 0.00122 -0.0301 0.6951 1.0000
0.250 0.2085 0.00554 0.00121 -0.0299 0.6780 1.0000
0.500 0.2363 0.00560 0.00118 -0.0297 0.6591 1.0000
0.750 0.2639 0.00568 0.00115 -0.0295 0.6385 1.0000
1.000 0.2915 0.00578 0.00114 -0.0293 0.6163 1.0000
1.250 0.3190 0.00590 0.00114 -0.0291 0.5928 1.0000
1.500 0.3464 0.00603 0.00116 -0.0289 0.5674 1.0000
1.750 0.3739 0.00617 0.00119 -0.0287 0.5415 1.0000
2.000 0.4014 0.00633 0.00123 -0.0286 0.5153 1.0000
2.250 0.4289 0.00650 0.00129 -0.0284 0.4886 1.0000
2.500 0.4563 0.00668 0.00138 -0.0283 0.4614 1.0000
2.750 0.4837 0.00688 0.00146 -0.0282 0.4343 1.0000
3.000 0.5111 0.00709 0.00157 -0.0280 0.4067 1.0000
3.250 0.5385 0.00731 0.00169 -0.0279 0.3796 1.0000
3.500 0.5658 0.00754 0.00184 -0.0278 0.3522 1.0000
3.750 0.5930 0.00779 0.00199 -0.0277 0.3256 1.0000
4.000 0.6202 0.00806 0.00216 -0.0276 0.2988 1.0000
4.250 0.6473 0.00833 0.00235 -0.0275 0.2734 1.0000
4.500 0.6744 0.00862 0.00257 -0.0274 0.2472 1.0000
4.750 0.7014 0.00892 0.00280 -0.0273 0.2234 1.0000
5.000 0.7283 0.00925 0.00305 -0.0272 0.1991 1.0000
5.250 0.7550 0.00961 0.00332 -0.0271 0.1769 1.0000
5.500 0.7818 0.00995 0.00361 -0.0270 0.1555 1.0000
5.750 0.8083 0.01035 0.00396 -0.0268 0.1362 1.0000
6.000 0.8348 0.01072 0.00430 -0.0267 0.1183 1.0000
6.250 0.8612 0.01113 0.00467 -0.0265 0.1018 1.0000
6.500 0.8873 0.01159 0.00508 -0.0264 0.0860 1.0000
6.750 0.9133 0.01209 0.00555 -0.0262 0.0715 1.0000
7.000 0.9389 0.01263 0.00607 -0.0260 0.0581 1.0000
7.250 0.9643 0.01324 0.00666 -0.0257 0.0465 1.0000
7.500 0.9899 0.01378 0.00722 -0.0255 0.0381 1.0000
7.750 1.0151 0.01440 0.00790 -0.0252 0.0311 1.0000
8.000 1.0387 0.01540 0.00896 -0.0247 0.0251 1.0000
8.250 1.0636 0.01603 0.00970 -0.0243 0.0216 1.0000
8.500 1.0844 0.01760 0.01138 -0.0236 0.0177 1.0000
8.750 1.1092 0.01817 0.01205 -0.0233 0.0161 1.0000
9.000 1.1323 0.01907 0.01307 -0.0228 0.0144 1.0000
9.250 1.1538 0.02026 0.01435 -0.0222 0.0130 1.0000
9.500 1.1666 0.02326 0.01764 -0.0208 0.0117 1.0000
9.750 1.1893 0.02403 0.01854 -0.0203 0.0110 1.0000
10.000 1.2102 0.02506 0.01975 -0.0197 0.0101 1.0000
10.250 1.2292 0.02638 0.02122 -0.0190 0.0094 1.0000
10.500 1.2464 0.02788 0.02287 -0.0183 0.0088 1.0000
10.750 1.2607 0.02973 0.02488 -0.0174 0.0083 1.0000
11.000 1.2670 0.03274 0.02815 -0.0161 0.0079 1.0000
11.250 1.2607 0.03736 0.03316 -0.0144 0.0076 1.0000
11.750 1.2380 0.04524 0.04161 -0.0124 0.0075 1.0000
12.000 1.2304 0.04928 0.04588 -0.0145 0.0074 1.0000
12.250 1.2182 0.05496 0.05177 -0.0185 0.0074 1.0000
12.500 1.2045 0.06154 0.05855 -0.0234 0.0074 1.0000
12.750 1.1865 0.06937 0.06655 -0.0291 0.0074 1.0000
13.000 1.1620 0.07866 0.07600 -0.0354 0.0075 1.0000
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Polar data table (+)
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