AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG455ct -02f rot. (ag455ct02r-il) Reynolds number: 200,000 Max Cl/Cd: 58.33 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag455ct02r-il-200000-n5.txt Download as CSV file: xf-ag455ct02r-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5698 0.10302 0.09962 0.0159 1.0000 0.0209
-8.250 -0.5655 0.09892 0.09554 0.0135 1.0000 0.0209
-8.000 -0.5612 0.09474 0.09139 0.0108 1.0000 0.0209
-7.000 -0.5387 0.07270 0.06940 -0.0044 1.0000 0.0134
-6.750 -0.5271 0.06774 0.06440 -0.0089 1.0000 0.0129
-6.500 -0.5120 0.06207 0.05867 -0.0143 1.0000 0.0124
-6.250 -0.4943 0.05589 0.05236 -0.0196 1.0000 0.0120
-6.000 -0.4743 0.04923 0.04551 -0.0243 1.0000 0.0115
-5.750 -0.4526 0.04214 0.03809 -0.0281 1.0000 0.0111
-5.500 -0.4298 0.03530 0.03080 -0.0304 1.0000 0.0108
-5.250 -0.4060 0.02957 0.02448 -0.0315 1.0000 0.0108
-5.000 -0.3810 0.02588 0.02028 -0.0318 1.0000 0.0115
-4.750 -0.3548 0.02325 0.01715 -0.0317 1.0000 0.0130
-4.500 -0.3283 0.02088 0.01429 -0.0314 1.0000 0.0135
-4.250 -0.3018 0.01883 0.01184 -0.0311 1.0000 0.0137
-4.000 -0.2751 0.01722 0.00994 -0.0307 1.0000 0.0139
-3.750 -0.2490 0.01544 0.00797 -0.0302 1.0000 0.0144
-3.500 -0.2228 0.01425 0.00667 -0.0299 1.0000 0.0154
-3.250 -0.1964 0.01340 0.00577 -0.0295 1.0000 0.0167
-3.000 -0.1699 0.01272 0.00503 -0.0291 1.0000 0.0192
-2.750 -0.1435 0.01205 0.00433 -0.0288 1.0000 0.0239
-2.500 -0.1167 0.01151 0.00372 -0.0284 1.0000 0.0299
-2.250 -0.0901 0.01093 0.00321 -0.0282 1.0000 0.0478
-2.000 -0.0552 0.01033 0.00285 -0.0299 0.9836 0.1036
-1.750 -0.0177 0.00970 0.00262 -0.0322 0.9493 0.2078
-1.500 0.0195 0.00903 0.00242 -0.0344 0.8983 0.3558
-1.250 0.0480 0.00828 0.00225 -0.0343 0.8383 0.5623
-1.000 0.0662 0.00768 0.00221 -0.0312 0.7922 0.7756
-0.500 0.1289 0.00760 0.00194 -0.0311 0.7332 1.0000
-0.250 0.1554 0.00776 0.00187 -0.0306 0.7135 1.0000
0.000 0.1823 0.00790 0.00184 -0.0302 0.6954 1.0000
0.250 0.2095 0.00802 0.00182 -0.0299 0.6759 1.0000
0.500 0.2367 0.00812 0.00180 -0.0296 0.6552 1.0000
0.750 0.2638 0.00824 0.00178 -0.0293 0.6339 1.0000
1.000 0.2908 0.00836 0.00177 -0.0290 0.6110 1.0000
1.250 0.3179 0.00850 0.00178 -0.0287 0.5872 1.0000
1.500 0.3449 0.00865 0.00180 -0.0283 0.5626 1.0000
1.750 0.3718 0.00882 0.00184 -0.0280 0.5372 1.0000
2.000 0.3988 0.00900 0.00190 -0.0278 0.5110 1.0000
2.250 0.4258 0.00919 0.00197 -0.0275 0.4842 1.0000
2.500 0.4527 0.00940 0.00209 -0.0272 0.4572 1.0000
2.750 0.4797 0.00963 0.00220 -0.0270 0.4301 1.0000
3.000 0.5066 0.00987 0.00234 -0.0268 0.4035 1.0000
3.250 0.5335 0.01013 0.00250 -0.0266 0.3769 1.0000
3.500 0.5603 0.01040 0.00268 -0.0264 0.3507 1.0000
3.750 0.5871 0.01069 0.00292 -0.0262 0.3250 1.0000
4.000 0.6138 0.01100 0.00314 -0.0261 0.2995 1.0000
4.250 0.6405 0.01132 0.00340 -0.0259 0.2745 1.0000
4.500 0.6671 0.01165 0.00368 -0.0257 0.2503 1.0000
4.750 0.6936 0.01202 0.00402 -0.0256 0.2270 1.0000
5.000 0.7200 0.01241 0.00436 -0.0254 0.2046 1.0000
5.250 0.7464 0.01280 0.00472 -0.0252 0.1832 1.0000
5.500 0.7725 0.01325 0.00513 -0.0251 0.1630 1.0000
5.750 0.7986 0.01369 0.00559 -0.0249 0.1442 1.0000
6.000 0.8245 0.01418 0.00606 -0.0247 0.1264 1.0000
6.250 0.8502 0.01470 0.00657 -0.0245 0.1103 1.0000
6.500 0.8757 0.01526 0.00713 -0.0243 0.0951 1.0000
6.750 0.9011 0.01583 0.00773 -0.0240 0.0816 1.0000
7.000 0.9261 0.01646 0.00841 -0.0238 0.0685 1.0000
7.250 0.9508 0.01717 0.00914 -0.0235 0.0574 1.0000
7.500 0.9752 0.01792 0.00993 -0.0232 0.0472 1.0000
7.750 0.9995 0.01867 0.01080 -0.0228 0.0396 1.0000
8.000 1.0229 0.01960 0.01180 -0.0224 0.0331 1.0000
8.250 1.0459 0.02055 0.01288 -0.0220 0.0278 1.0000
8.500 1.0677 0.02177 0.01425 -0.0214 0.0243 1.0000
8.750 1.0901 0.02277 0.01541 -0.0209 0.0209 1.0000
9.000 1.1095 0.02429 0.01704 -0.0204 0.0180 1.0000
9.250 1.1292 0.02576 0.01872 -0.0196 0.0167 1.0000
9.500 1.1479 0.02733 0.02052 -0.0188 0.0153 1.0000
9.750 1.1664 0.02880 0.02218 -0.0182 0.0139 1.0000
10.000 1.1835 0.03030 0.02382 -0.0176 0.0126 1.0000
10.250 1.1950 0.03273 0.02650 -0.0167 0.0115 1.0000
10.500 1.2074 0.03492 0.02899 -0.0157 0.0110 1.0000
10.750 1.2164 0.03745 0.03183 -0.0147 0.0105 1.0000
11.000 1.2214 0.04025 0.03494 -0.0137 0.0101 1.0000
11.250 1.2213 0.04328 0.03826 -0.0128 0.0097 1.0000
11.500 1.2146 0.04655 0.04180 -0.0121 0.0095 1.0000
11.750 1.2049 0.05072 0.04622 -0.0134 0.0094 1.0000
12.000 1.1934 0.05605 0.05179 -0.0168 0.0093 1.0000
12.250 1.1794 0.06243 0.05841 -0.0214 0.0093 1.0000
12.500 1.1628 0.06989 0.06608 -0.0269 0.0093 1.0000
12.750 1.1432 0.07837 0.07476 -0.0329 0.0094 1.0000
13.000 1.1210 0.08774 0.08428 -0.0391 0.0096 1.0000
13.250 1.0962 0.09796 0.09465 -0.0455 0.0098 1.0000
13.500 1.0694 0.10890 0.10569 -0.0517 0.0101 1.0000
13.750 1.0392 0.12111 0.11797 -0.0583 0.0105 1.0000
14.000 1.0073 0.13458 0.13143 -0.0652 0.0110 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG455ct -02f rot. (ag455ct02r-il)