AG11 (ag11-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG11 (ag11-il) Reynolds number: 200,000 Max Cl/Cd: 59.91 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag11-il-200000.txt Download as CSV file: xf-ag11-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG11
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5202 0.10051 0.09707 0.0142 1.0000 0.0244
-7.750 -0.5150 0.09706 0.09365 0.0123 1.0000 0.0250
-7.500 -0.5100 0.09360 0.09022 0.0101 1.0000 0.0256
-7.250 -0.5045 0.09007 0.08673 0.0073 1.0000 0.0262
-7.000 -0.4948 0.08615 0.08283 0.0029 1.0000 0.0270
-6.750 -0.4812 0.08202 0.07868 -0.0027 1.0000 0.0278
-6.500 -0.4602 0.07771 0.07432 -0.0111 1.0000 0.0288
-6.250 -0.4349 0.07364 0.07014 -0.0187 1.0000 0.0293
-6.000 -0.4131 0.06980 0.06617 -0.0229 1.0000 0.0295
-5.750 -0.3922 0.06598 0.06220 -0.0259 1.0000 0.0296
-5.500 -0.3881 0.05892 0.05526 -0.0265 1.0000 0.0308
-5.250 -0.3736 0.05552 0.05187 -0.0270 1.0000 0.0319
-5.000 -0.3544 0.05219 0.04847 -0.0283 1.0000 0.0333
-4.750 -0.3319 0.04875 0.04493 -0.0302 1.0000 0.0353
-4.500 -0.3060 0.04533 0.04133 -0.0321 1.0000 0.0380
-4.250 -0.2676 0.04457 0.03995 -0.0337 1.0000 0.0412
-4.000 -0.2521 0.03802 0.03344 -0.0351 1.0000 0.0430
-3.750 -0.2318 0.03533 0.03076 -0.0352 1.0000 0.0454
-3.500 -0.2073 0.03301 0.02826 -0.0354 1.0000 0.0498
-3.250 -0.1794 0.03034 0.02516 -0.0355 1.0000 0.0564
-3.000 -0.1580 0.02806 0.02289 -0.0354 1.0000 0.0604
-1.750 -0.0256 0.01715 0.01037 -0.0304 1.0000 0.0365
-1.500 -0.0005 0.01592 0.00892 -0.0294 1.0000 0.0376
-1.250 0.0254 0.01460 0.00743 -0.0286 1.0000 0.0367
-1.000 0.0517 0.01345 0.00617 -0.0279 1.0000 0.0353
-0.750 0.0916 0.01234 0.00504 -0.0301 0.9954 0.0363
-0.500 0.1381 0.01133 0.00403 -0.0337 0.9864 0.0433
-0.250 0.1759 0.00773 0.00329 -0.0353 0.9818 1.0000
0.000 0.2221 0.00769 0.00297 -0.0388 0.9659 1.0000
0.250 0.2638 0.00765 0.00278 -0.0414 0.9456 1.0000
0.500 0.2985 0.00762 0.00262 -0.0422 0.9196 1.0000
0.750 0.3267 0.00763 0.00251 -0.0416 0.8895 1.0000
1.000 0.3515 0.00769 0.00242 -0.0402 0.8571 1.0000
1.250 0.3755 0.00779 0.00237 -0.0387 0.8219 1.0000
1.500 0.3997 0.00793 0.00232 -0.0373 0.7859 1.0000
1.750 0.4244 0.00811 0.00232 -0.0362 0.7477 1.0000
2.000 0.4494 0.00832 0.00233 -0.0352 0.7091 1.0000
2.250 0.4747 0.00856 0.00238 -0.0343 0.6692 1.0000
2.500 0.5002 0.00882 0.00245 -0.0335 0.6282 1.0000
2.750 0.5258 0.00911 0.00254 -0.0329 0.5856 1.0000
3.000 0.5516 0.00942 0.00265 -0.0323 0.5413 1.0000
3.250 0.5773 0.00976 0.00279 -0.0318 0.4968 1.0000
3.500 0.6031 0.01012 0.00296 -0.0314 0.4528 1.0000
3.750 0.6289 0.01052 0.00318 -0.0310 0.4101 1.0000
4.000 0.6548 0.01093 0.00341 -0.0307 0.3700 1.0000
4.250 0.6806 0.01137 0.00368 -0.0304 0.3324 1.0000
4.500 0.7065 0.01180 0.00398 -0.0302 0.2974 1.0000
4.750 0.7322 0.01227 0.00435 -0.0299 0.2640 1.0000
5.000 0.7578 0.01279 0.00472 -0.0297 0.2336 1.0000
5.250 0.7833 0.01333 0.00515 -0.0295 0.2058 1.0000
5.500 0.8087 0.01391 0.00564 -0.0292 0.1794 1.0000
5.750 0.8339 0.01451 0.00620 -0.0289 0.1559 1.0000
6.000 0.8585 0.01527 0.00684 -0.0286 0.1375 1.0000
6.250 0.8829 0.01608 0.00759 -0.0281 0.1230 1.0000
6.500 0.9077 0.01679 0.00831 -0.0278 0.1113 1.0000
6.750 0.9326 0.01748 0.00910 -0.0273 0.1015 1.0000
7.000 0.9565 0.01848 0.01011 -0.0268 0.0942 1.0000
7.250 0.9810 0.01928 0.01097 -0.0264 0.0879 1.0000
7.500 1.0043 0.02051 0.01223 -0.0258 0.0824 1.0000
7.750 1.0287 0.02127 0.01316 -0.0253 0.0768 1.0000
8.000 1.0515 0.02275 0.01462 -0.0248 0.0723 1.0000
8.250 1.0751 0.02404 0.01616 -0.0242 0.0690 1.0000
8.500 1.0983 0.02514 0.01748 -0.0236 0.0651 1.0000
8.750 1.1206 0.02637 0.01873 -0.0231 0.0612 1.0000
9.000 1.1409 0.02875 0.02139 -0.0224 0.0584 1.0000
9.250 1.1617 0.03036 0.02340 -0.0215 0.0557 1.0000
9.500 1.1818 0.03171 0.02498 -0.0207 0.0524 1.0000
9.750 1.2010 0.03335 0.02668 -0.0202 0.0495 1.0000
10.000 1.2119 0.03742 0.03119 -0.0190 0.0475 1.0000
10.250 1.2247 0.03953 0.03380 -0.0176 0.0454 1.0000
10.500 1.2357 0.04183 0.03647 -0.0164 0.0428 1.0000
10.750 1.2462 0.04404 0.03891 -0.0153 0.0408 1.0000
11.000 1.2570 0.04601 0.04095 -0.0144 0.0388 1.0000
11.500 1.2315 0.05586 0.05158 -0.0113 0.0371 1.0000
11.750 1.2125 0.05944 0.05545 -0.0097 0.0368 1.0000
12.000 1.1897 0.06442 0.06063 -0.0105 0.0369 1.0000
12.250 1.1643 0.07113 0.06753 -0.0139 0.0372 1.0000
12.500 1.0049 0.11668 0.11344 -0.0482 0.0495 1.0000
12.750 0.9228 0.15021 0.14671 -0.0666 0.0748 1.0000
13.000 0.9348 0.15246 0.14901 -0.0651 0.0731 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG11 (ag11-il)