AG13 (ag13-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG13 (ag13-il) Reynolds number: 100,000 Max Cl/Cd: 47.3 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag13-il-100000-n5.txt Download as CSV file: xf-ag13-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG13
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5845 0.13348 0.12844 0.0268 1.0000 0.0356
-10.000 -0.5829 0.13051 0.12550 0.0236 1.0000 0.0366
-9.750 -0.5806 0.12728 0.12232 0.0205 1.0000 0.0369
-9.000 -0.5690 0.11633 0.11142 0.0130 1.0000 0.0374
-8.750 -0.5649 0.11251 0.10764 0.0104 1.0000 0.0374
-8.500 -0.5604 0.10862 0.10379 0.0078 1.0000 0.0375
-8.250 -0.5491 0.10348 0.09865 0.0138 1.0000 0.0409
-8.000 -0.5432 0.10011 0.09532 0.0126 1.0000 0.0430
-7.750 -0.5386 0.09654 0.09179 0.0105 1.0000 0.0447
-7.500 -0.5344 0.09282 0.08812 0.0078 1.0000 0.0460
-7.250 -0.5275 0.08851 0.08386 -0.0006 1.0000 0.0490
-7.000 -0.5104 0.08273 0.07806 -0.0136 1.0000 0.0499
-6.750 -0.4950 0.07716 0.07244 -0.0195 1.0000 0.0499
-6.500 -0.4873 0.06875 0.06404 -0.0174 1.0000 0.0248
-6.250 -0.4718 0.06353 0.05877 -0.0219 1.0000 0.0240
-6.000 -0.4523 0.05758 0.05273 -0.0275 1.0000 0.0232
-5.750 -0.4297 0.05119 0.04614 -0.0332 1.0000 0.0224
-5.500 -0.4049 0.04465 0.03929 -0.0383 1.0000 0.0217
-5.250 -0.3786 0.03860 0.03280 -0.0421 1.0000 0.0211
-5.000 -0.3512 0.03328 0.02692 -0.0446 1.0000 0.0208
-4.750 -0.3233 0.02894 0.02195 -0.0461 1.0000 0.0207
-4.500 -0.2952 0.02553 0.01793 -0.0467 1.0000 0.0211
-4.250 -0.2672 0.02292 0.01479 -0.0468 1.0000 0.0221
-4.000 -0.2394 0.02128 0.01265 -0.0466 1.0000 0.0253
-3.750 -0.2125 0.01917 0.01029 -0.0464 1.0000 0.0277
-3.500 -0.1859 0.01770 0.00869 -0.0461 1.0000 0.0304
-3.250 -0.1591 0.01651 0.00735 -0.0456 1.0000 0.0349
-3.000 -0.1325 0.01554 0.00634 -0.0454 1.0000 0.0452
-2.750 -0.1056 0.01460 0.00533 -0.0451 1.0000 0.0616
-2.500 -0.0788 0.01368 0.00456 -0.0449 1.0000 0.1020
-2.250 -0.0525 0.01286 0.00411 -0.0449 1.0000 0.1849
-2.000 -0.0267 0.01218 0.00386 -0.0448 1.0000 0.2977
-1.750 -0.0012 0.01163 0.00368 -0.0444 1.0000 0.4160
-1.500 0.0239 0.01110 0.00354 -0.0438 1.0000 0.5410
-1.000 0.0691 0.00980 0.00316 -0.0403 1.0000 1.0000
-0.750 0.0954 0.00985 0.00304 -0.0401 1.0000 1.0000
-0.500 0.1214 0.00992 0.00298 -0.0399 1.0000 1.0000
0.000 0.1942 0.01010 0.00290 -0.0438 0.9773 1.0000
0.250 0.2359 0.01016 0.00288 -0.0466 0.9541 1.0000
0.500 0.2750 0.01022 0.00286 -0.0486 0.9262 1.0000
0.750 0.3112 0.01027 0.00284 -0.0499 0.8929 1.0000
1.000 0.3442 0.01035 0.00282 -0.0504 0.8554 1.0000
1.250 0.3733 0.01047 0.00282 -0.0499 0.8148 1.0000
1.500 0.4001 0.01063 0.00284 -0.0490 0.7729 1.0000
1.750 0.4259 0.01084 0.00292 -0.0480 0.7306 1.0000
2.000 0.4515 0.01108 0.00301 -0.0470 0.6884 1.0000
2.250 0.4773 0.01136 0.00312 -0.0461 0.6465 1.0000
2.500 0.5030 0.01166 0.00326 -0.0453 0.6049 1.0000
2.750 0.5287 0.01198 0.00344 -0.0446 0.5638 1.0000
3.000 0.5544 0.01233 0.00370 -0.0439 0.5231 1.0000
3.250 0.5801 0.01270 0.00393 -0.0433 0.4829 1.0000
3.500 0.6058 0.01310 0.00421 -0.0428 0.4430 1.0000
3.750 0.6314 0.01352 0.00451 -0.0423 0.4034 1.0000
4.000 0.6570 0.01398 0.00485 -0.0418 0.3645 1.0000
4.250 0.6826 0.01446 0.00530 -0.0414 0.3263 1.0000
4.500 0.7081 0.01497 0.00573 -0.0410 0.2900 1.0000
4.750 0.7334 0.01553 0.00622 -0.0406 0.2551 1.0000
5.000 0.7588 0.01612 0.00676 -0.0402 0.2220 1.0000
5.250 0.7839 0.01676 0.00736 -0.0399 0.1914 1.0000
5.500 0.8088 0.01747 0.00808 -0.0395 0.1629 1.0000
5.750 0.8336 0.01822 0.00884 -0.0391 0.1382 1.0000
6.000 0.8581 0.01904 0.00967 -0.0387 0.1148 1.0000
6.250 0.8821 0.01999 0.01062 -0.0383 0.0962 1.0000
6.500 0.9060 0.02097 0.01166 -0.0378 0.0779 1.0000
6.750 0.9292 0.02213 0.01291 -0.0372 0.0640 1.0000
7.000 0.9520 0.02335 0.01430 -0.0366 0.0511 1.0000
7.250 0.9735 0.02492 0.01598 -0.0359 0.0425 1.0000
7.500 0.9945 0.02644 0.01759 -0.0353 0.0341 1.0000
7.750 1.0153 0.02843 0.01991 -0.0342 0.0298 1.0000
8.000 1.0355 0.03003 0.02165 -0.0335 0.0249 1.0000
8.250 1.0533 0.03258 0.02450 -0.0325 0.0221 1.0000
8.500 1.0706 0.03552 0.02788 -0.0313 0.0204 1.0000
8.750 1.0853 0.03885 0.03167 -0.0302 0.0191 1.0000
9.000 1.0974 0.04212 0.03538 -0.0292 0.0178 1.0000
9.250 1.1081 0.04474 0.03827 -0.0286 0.0164 1.0000
9.500 1.1116 0.04843 0.04231 -0.0279 0.0153 1.0000
9.750 1.1080 0.05308 0.04739 -0.0273 0.0147 1.0000
10.000 1.1006 0.05756 0.05230 -0.0271 0.0145 1.0000
10.250 1.0858 0.06214 0.05717 -0.0274 0.0144 1.0000
10.500 1.0684 0.06769 0.06294 -0.0303 0.0145 1.0000
10.750 1.0509 0.07481 0.07023 -0.0361 0.0147 1.0000
11.000 1.0332 0.08328 0.07873 -0.0430 0.0150 1.0000
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Polar data table (+)
Polar graphs
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