AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG455ct -02f rot. (ag455ct02r-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.94 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag455ct02r-il-1000000.txt Download as CSV file: xf-ag455ct02r-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5889 0.10375 0.10220 0.0261 1.0000 0.0078
-8.500 -0.5851 0.09978 0.09824 0.0240 1.0000 0.0082
-8.250 -0.5813 0.09553 0.09401 0.0214 1.0000 0.0086
-8.000 -0.5769 0.09118 0.08967 0.0182 1.0000 0.0089
-7.750 -0.5720 0.08713 0.08564 0.0153 1.0000 0.0090
-7.500 -0.5657 0.08264 0.08116 0.0109 1.0000 0.0091
-7.250 -0.5543 0.07734 0.07586 0.0045 1.0000 0.0091
-7.000 -0.5400 0.07157 0.07008 -0.0025 1.0000 0.0091
-6.750 -0.5232 0.06545 0.06392 -0.0095 1.0000 0.0091
-6.500 -0.5043 0.05908 0.05748 -0.0158 1.0000 0.0092
-6.250 -0.4839 0.05254 0.05083 -0.0211 1.0000 0.0092
-6.000 -0.4625 0.04587 0.04400 -0.0253 1.0000 0.0092
-5.750 -0.4475 0.03318 0.03081 -0.0306 1.0000 0.0096
-5.500 -0.4263 0.02909 0.02645 -0.0318 1.0000 0.0099
-5.250 -0.4029 0.02657 0.02374 -0.0323 1.0000 0.0103
-5.000 -0.3786 0.02399 0.02093 -0.0325 1.0000 0.0107
-4.750 -0.3531 0.01681 0.01293 -0.0319 1.0000 0.0080
-4.500 -0.3270 0.01256 0.00802 -0.0312 1.0000 0.0073
-4.250 -0.3004 0.01153 0.00685 -0.0308 1.0000 0.0080
-4.000 -0.2737 0.01077 0.00598 -0.0303 1.0000 0.0085
-3.750 -0.2471 0.01012 0.00525 -0.0299 1.0000 0.0089
-3.500 -0.2205 0.00957 0.00463 -0.0295 1.0000 0.0091
-3.250 -0.1901 0.00856 0.00351 -0.0300 0.9970 0.0096
-3.000 -0.1520 0.00783 0.00270 -0.0322 0.9824 0.0107
-2.750 -0.1145 0.00740 0.00219 -0.0340 0.9432 0.0117
-2.500 -0.0911 0.00739 0.00184 -0.0324 0.8426 0.0135
-2.250 -0.0659 0.00732 0.00146 -0.0315 0.7713 0.0209
-2.000 -0.0388 0.00712 0.00124 -0.0313 0.7414 0.0496
-1.750 -0.0114 0.00693 0.00112 -0.0312 0.7235 0.0942
-1.500 0.0161 0.00666 0.00103 -0.0311 0.7102 0.1664
-1.250 0.0437 0.00640 0.00096 -0.0311 0.6987 0.2442
-1.000 0.0713 0.00603 0.00091 -0.0312 0.6856 0.3566
-0.750 0.0987 0.00558 0.00086 -0.0312 0.6708 0.5010
-0.500 0.1247 0.00499 0.00083 -0.0310 0.6541 0.7033
-0.250 0.1480 0.00456 0.00083 -0.0297 0.6360 0.8575
0.000 0.1734 0.00436 0.00080 -0.0286 0.6160 0.9719
0.250 0.2067 0.00444 0.00076 -0.0297 0.5932 1.0000
0.500 0.2346 0.00454 0.00074 -0.0296 0.5702 1.0000
0.750 0.2625 0.00465 0.00074 -0.0295 0.5466 1.0000
1.000 0.2903 0.00478 0.00075 -0.0294 0.5223 1.0000
1.250 0.3181 0.00490 0.00077 -0.0293 0.4977 1.0000
1.500 0.3460 0.00504 0.00080 -0.0292 0.4727 1.0000
1.750 0.3738 0.00518 0.00084 -0.0291 0.4481 1.0000
2.000 0.4016 0.00534 0.00088 -0.0290 0.4234 1.0000
2.250 0.4294 0.00551 0.00094 -0.0290 0.3983 1.0000
2.500 0.4572 0.00567 0.00102 -0.0289 0.3738 1.0000
2.750 0.4849 0.00585 0.00110 -0.0289 0.3493 1.0000
3.000 0.5125 0.00604 0.00120 -0.0288 0.3255 1.0000
3.250 0.5402 0.00624 0.00130 -0.0287 0.3013 1.0000
3.500 0.5678 0.00644 0.00143 -0.0287 0.2779 1.0000
3.750 0.5953 0.00665 0.00156 -0.0286 0.2562 1.0000
4.000 0.6228 0.00689 0.00170 -0.0286 0.2324 1.0000
4.250 0.6502 0.00711 0.00185 -0.0285 0.2124 1.0000
4.750 0.7049 0.00762 0.00222 -0.0284 0.1715 1.0000
5.000 0.7320 0.00791 0.00242 -0.0283 0.1510 1.0000
5.250 0.7592 0.00818 0.00264 -0.0282 0.1343 1.0000
5.500 0.7863 0.00846 0.00288 -0.0281 0.1177 1.0000
5.750 0.8133 0.00876 0.00313 -0.0280 0.1029 1.0000
6.000 0.8401 0.00909 0.00340 -0.0279 0.0883 1.0000
6.250 0.8668 0.00943 0.00368 -0.0278 0.0751 1.0000
6.500 0.8935 0.00978 0.00400 -0.0277 0.0628 1.0000
6.750 0.9200 0.01014 0.00434 -0.0276 0.0523 1.0000
7.000 0.9464 0.01053 0.00470 -0.0274 0.0425 1.0000
7.250 0.9726 0.01096 0.00511 -0.0272 0.0340 1.0000
7.500 0.9983 0.01150 0.00562 -0.0270 0.0258 1.0000
7.750 1.0245 0.01187 0.00601 -0.0268 0.0219 1.0000
8.000 1.0500 0.01246 0.00664 -0.0265 0.0172 1.0000
8.250 1.0757 0.01292 0.00712 -0.0263 0.0147 1.0000
8.500 1.0998 0.01382 0.00812 -0.0259 0.0116 1.0000
8.750 1.1254 0.01425 0.00861 -0.0256 0.0107 1.0000
9.000 1.1504 0.01477 0.00918 -0.0254 0.0095 1.0000
9.250 1.1736 0.01571 0.01019 -0.0249 0.0080 1.0000
9.500 1.1963 0.01671 0.01134 -0.0244 0.0073 1.0000
9.750 1.2204 0.01734 0.01207 -0.0240 0.0068 1.0000
10.000 1.2437 0.01809 0.01292 -0.0236 0.0063 1.0000
10.250 1.2665 0.01888 0.01379 -0.0232 0.0058 1.0000
10.500 1.2882 0.01984 0.01484 -0.0227 0.0054 1.0000
10.750 1.3044 0.02174 0.01695 -0.0217 0.0049 1.0000
11.000 1.3173 0.02406 0.01953 -0.0205 0.0046 1.0000
11.250 1.3375 0.02499 0.02057 -0.0200 0.0044 1.0000
11.500 1.3563 0.02608 0.02179 -0.0193 0.0042 1.0000
11.750 1.3735 0.02730 0.02315 -0.0186 0.0040 1.0000
12.000 1.3898 0.02854 0.02453 -0.0179 0.0037 1.0000
12.250 1.4042 0.02991 0.02601 -0.0171 0.0035 1.0000
12.500 1.4166 0.03139 0.02761 -0.0163 0.0033 1.0000
12.750 1.4243 0.03326 0.02962 -0.0153 0.0032 1.0000
13.000 1.4227 0.03551 0.03202 -0.0138 0.0031 1.0000
13.250 1.4144 0.03878 0.03546 -0.0138 0.0031 1.0000
13.500 1.4043 0.04379 0.04067 -0.0171 0.0030 1.0000
13.750 1.3914 0.05013 0.04719 -0.0218 0.0030 1.0000
14.000 1.3748 0.05759 0.05483 -0.0272 0.0030 1.0000
14.250 1.3545 0.06587 0.06328 -0.0326 0.0031 1.0000
14.500 1.3306 0.07479 0.07235 -0.0379 0.0031 1.0000
14.750 1.3038 0.08415 0.08185 -0.0429 0.0031 1.0000
15.000 1.2735 0.09415 0.09198 -0.0480 0.0032 1.0000
15.250 1.2374 0.10538 0.10336 -0.0536 0.0033 1.0000
15.500 1.2063 0.11610 0.11420 -0.0589 0.0034 1.0000
15.750 1.1717 0.12810 0.12632 -0.0648 0.0035 1.0000
16.000 1.1385 0.14057 0.13889 -0.0711 0.0037 1.0000
16.250 1.0998 0.15541 0.15387 -0.0786 0.0039 1.0000
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Polar data table (+)
Polar graphs
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