AG45ct -02f (ag45ct02r-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG45ct -02f (ag45ct02r-il) Reynolds number: 100,000 Max Cl/Cd: 46.78 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag45ct02r-il-100000-n5.txt Download as CSV file: xf-ag45ct02r-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5945 0.13580 0.13079 0.0281 1.0000 0.0393
-10.250 -0.5931 0.13249 0.12752 0.0249 1.0000 0.0397
-10.000 -0.5907 0.12892 0.12398 0.0221 1.0000 0.0399
-9.750 -0.5875 0.12518 0.12028 0.0195 1.0000 0.0401
-9.500 -0.5842 0.12132 0.11646 0.0170 1.0000 0.0402
-9.250 -0.5809 0.11735 0.11252 0.0145 1.0000 0.0402
-9.000 -0.5775 0.11328 0.10849 0.0119 1.0000 0.0403
-8.750 -0.5735 0.10912 0.10437 0.0094 1.0000 0.0403
-8.500 -0.5692 0.10486 0.10014 0.0067 1.0000 0.0403
-8.250 -0.5661 0.09964 0.09500 0.0055 1.0000 0.0406
-8.000 -0.5561 0.09592 0.09127 0.0101 1.0000 0.0424
-7.750 -0.5490 0.09273 0.08811 0.0098 1.0000 0.0444
-7.250 -0.5344 0.07867 0.07404 -0.0076 1.0000 0.0286
-7.000 -0.5260 0.07404 0.06940 -0.0100 1.0000 0.0281
-6.750 -0.5152 0.06905 0.06439 -0.0136 1.0000 0.0276
-6.500 -0.5025 0.06386 0.05912 -0.0174 1.0000 0.0267
-6.250 -0.4875 0.05830 0.05345 -0.0214 1.0000 0.0256
-6.000 -0.4701 0.05229 0.04723 -0.0253 1.0000 0.0244
-5.750 -0.4506 0.04592 0.04052 -0.0286 1.0000 0.0232
-5.500 -0.4293 0.03969 0.03380 -0.0308 1.0000 0.0221
-5.250 -0.4062 0.03421 0.02764 -0.0320 1.0000 0.0214
-5.000 -0.3822 0.03043 0.02327 -0.0323 1.0000 0.0213
-4.750 -0.3574 0.02740 0.01976 -0.0322 1.0000 0.0214
-4.500 -0.3319 0.02490 0.01684 -0.0319 1.0000 0.0219
-4.250 -0.3060 0.02281 0.01439 -0.0316 1.0000 0.0226
-4.000 -0.2799 0.02130 0.01263 -0.0312 1.0000 0.0249
-3.750 -0.2534 0.01997 0.01101 -0.0306 1.0000 0.0279
-3.500 -0.2274 0.01836 0.00921 -0.0300 1.0000 0.0298
-3.250 -0.2021 0.01705 0.00789 -0.0295 1.0000 0.0329
-3.000 -0.1762 0.01624 0.00696 -0.0289 1.0000 0.0400
-2.750 -0.1507 0.01522 0.00596 -0.0284 1.0000 0.0496
-2.500 -0.1251 0.01434 0.00518 -0.0280 1.0000 0.0732
-2.250 -0.0997 0.01340 0.00458 -0.0278 1.0000 0.1412
-2.000 -0.0749 0.01246 0.00427 -0.0277 1.0000 0.2812
-1.750 -0.0517 0.01144 0.00411 -0.0271 1.0000 0.4943
-1.500 -0.0332 0.01051 0.00407 -0.0245 1.0000 0.7350
-1.250 0.0202 0.01004 0.00376 -0.0286 0.9781 1.0000
-1.000 0.0621 0.01009 0.00354 -0.0315 0.9431 1.0000
-0.750 0.1018 0.01013 0.00335 -0.0338 0.9041 1.0000
-0.500 0.1372 0.01020 0.00317 -0.0349 0.8646 1.0000
-0.250 0.1676 0.01031 0.00303 -0.0349 0.8287 1.0000
0.000 0.1949 0.01045 0.00295 -0.0343 0.7974 1.0000
0.250 0.2213 0.01062 0.00290 -0.0336 0.7707 1.0000
0.500 0.2476 0.01080 0.00288 -0.0329 0.7468 1.0000
0.750 0.2740 0.01100 0.00290 -0.0323 0.7253 1.0000
1.000 0.3002 0.01121 0.00296 -0.0317 0.7056 1.0000
1.250 0.3269 0.01139 0.00305 -0.0312 0.6838 1.0000
1.500 0.3533 0.01156 0.00314 -0.0307 0.6623 1.0000
1.750 0.3798 0.01172 0.00322 -0.0303 0.6395 1.0000
2.000 0.4061 0.01189 0.00331 -0.0297 0.6164 1.0000
2.250 0.4323 0.01207 0.00339 -0.0292 0.5927 1.0000
2.500 0.4586 0.01225 0.00353 -0.0286 0.5673 1.0000
2.750 0.4847 0.01246 0.00365 -0.0281 0.5414 1.0000
3.000 0.5108 0.01270 0.00380 -0.0276 0.5151 1.0000
3.250 0.5369 0.01296 0.00398 -0.0271 0.4884 1.0000
3.500 0.5629 0.01324 0.00422 -0.0266 0.4615 1.0000
3.750 0.5888 0.01355 0.00446 -0.0262 0.4347 1.0000
4.000 0.6147 0.01388 0.00473 -0.0258 0.4081 1.0000
4.250 0.6405 0.01424 0.00503 -0.0253 0.3816 1.0000
4.500 0.6662 0.01462 0.00537 -0.0249 0.3554 1.0000
4.750 0.6919 0.01502 0.00579 -0.0246 0.3292 1.0000
5.000 0.7175 0.01545 0.00621 -0.0242 0.3037 1.0000
5.250 0.7429 0.01592 0.00666 -0.0238 0.2782 1.0000
5.500 0.7681 0.01642 0.00716 -0.0235 0.2529 1.0000
5.750 0.7931 0.01698 0.00773 -0.0231 0.2282 1.0000
6.000 0.8179 0.01756 0.00832 -0.0228 0.2034 1.0000
6.250 0.8426 0.01820 0.00898 -0.0224 0.1801 1.0000
6.500 0.8668 0.01891 0.00969 -0.0220 0.1580 1.0000
6.750 0.8908 0.01968 0.01053 -0.0217 0.1368 1.0000
7.000 0.9143 0.02053 0.01140 -0.0213 0.1177 1.0000
7.250 0.9375 0.02144 0.01237 -0.0208 0.0990 1.0000
7.500 0.9598 0.02249 0.01346 -0.0204 0.0835 1.0000
7.750 0.9814 0.02367 0.01466 -0.0199 0.0693 1.0000
8.000 1.0026 0.02493 0.01605 -0.0192 0.0584 1.0000
8.250 1.0232 0.02626 0.01757 -0.0186 0.0488 1.0000
8.500 1.0418 0.02794 0.01938 -0.0178 0.0427 1.0000
8.750 1.0608 0.02947 0.02108 -0.0170 0.0370 1.0000
9.000 1.0775 0.03138 0.02315 -0.0162 0.0327 1.0000
9.250 1.0942 0.03345 0.02551 -0.0152 0.0298 1.0000
9.500 1.1094 0.03550 0.02775 -0.0143 0.0273 1.0000
9.750 1.1203 0.03814 0.03047 -0.0134 0.0250 1.0000
10.000 1.1327 0.04055 0.03333 -0.0125 0.0231 1.0000
10.250 1.1406 0.04360 0.03677 -0.0115 0.0219 1.0000
10.500 1.1442 0.04693 0.04046 -0.0105 0.0210 1.0000
10.750 1.1429 0.05047 0.04439 -0.0098 0.0204 1.0000
11.000 1.1349 0.05410 0.04832 -0.0092 0.0200 1.0000
11.250 1.1228 0.05840 0.05288 -0.0101 0.0198 1.0000
11.500 1.1080 0.06377 0.05851 -0.0130 0.0198 1.0000
11.750 1.0902 0.07036 0.06534 -0.0175 0.0198 1.0000
12.000 1.0688 0.07848 0.07368 -0.0236 0.0201 1.0000
12.250 1.0430 0.08844 0.08378 -0.0311 0.0206 1.0000
12.500 1.0116 0.10071 0.09617 -0.0397 0.0214 1.0000
12.750 0.9781 0.11435 0.10986 -0.0480 0.0224 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG45ct -02f (ag45ct02r-il)