AG14 (ag14-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG14 (ag14-il) Reynolds number: 100,000 Max Cl/Cd: 47.58 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag14-il-100000-n5.txt Download as CSV file: xf-ag14-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG14
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5576 0.11695 0.11197 0.0201 1.0000 0.0362
-8.750 -0.5560 0.11415 0.10923 0.0159 1.0000 0.0372
-8.500 -0.5529 0.11103 0.10616 0.0122 1.0000 0.0376
-8.250 -0.5488 0.10765 0.10284 0.0088 1.0000 0.0378
-8.000 -0.5440 0.10404 0.09927 0.0050 1.0000 0.0379
-7.750 -0.5355 0.09834 0.09359 0.0107 1.0000 0.0404
-7.500 -0.5283 0.09504 0.09032 0.0101 1.0000 0.0425
-7.250 -0.5223 0.09153 0.08685 0.0079 1.0000 0.0440
-7.000 -0.5134 0.08757 0.08292 0.0042 1.0000 0.0451
-6.750 -0.5023 0.08330 0.07868 -0.0004 1.0000 0.0460
-6.500 -0.4773 0.07763 0.07296 -0.0157 1.0000 0.0501
-6.250 -0.4544 0.07198 0.06717 -0.0244 1.0000 0.0505
-6.000 -0.4533 0.06704 0.06236 -0.0175 1.0000 0.0323
-5.750 -0.4236 0.05842 0.05353 -0.0276 1.0000 0.0247
-5.500 -0.4021 0.05317 0.04816 -0.0318 1.0000 0.0237
-5.250 -0.3769 0.04753 0.04231 -0.0363 1.0000 0.0228
-5.000 -0.3494 0.04177 0.03624 -0.0404 1.0000 0.0220
-4.750 -0.3208 0.03633 0.03037 -0.0436 1.0000 0.0214
-4.500 -0.2915 0.03150 0.02500 -0.0457 1.0000 0.0210
-4.250 -0.2622 0.02747 0.02031 -0.0470 1.0000 0.0209
-4.000 -0.2332 0.02428 0.01653 -0.0475 1.0000 0.0213
-3.750 -0.2049 0.02215 0.01389 -0.0475 1.0000 0.0239
-3.500 -0.1767 0.02049 0.01178 -0.0472 1.0000 0.0263
-3.250 -0.1496 0.01826 0.00932 -0.0470 1.0000 0.0281
-3.000 -0.1228 0.01690 0.00784 -0.0466 1.0000 0.0310
-2.750 -0.0960 0.01591 0.00670 -0.0462 1.0000 0.0370
-2.500 -0.0694 0.01489 0.00562 -0.0459 1.0000 0.0469
-2.250 -0.0425 0.01401 0.00476 -0.0456 1.0000 0.0673
-2.000 -0.0157 0.01311 0.00411 -0.0455 1.0000 0.1212
-1.750 0.0105 0.01232 0.00377 -0.0454 1.0000 0.2320
-1.500 0.0364 0.01160 0.00358 -0.0453 1.0000 0.3871
-1.250 0.0606 0.01074 0.00341 -0.0445 1.0000 0.5926
-1.000 0.0808 0.00974 0.00317 -0.0418 1.0000 1.0000
-0.750 0.1071 0.00979 0.00302 -0.0415 1.0000 1.0000
-0.500 0.1332 0.00985 0.00292 -0.0413 1.0000 1.0000
-0.250 0.1592 0.00993 0.00288 -0.0410 1.0000 1.0000
0.000 0.1931 0.01002 0.00284 -0.0425 0.9918 1.0000
0.250 0.2362 0.01010 0.00282 -0.0456 0.9702 1.0000
0.500 0.2766 0.01016 0.00280 -0.0481 0.9436 1.0000
0.750 0.3152 0.01021 0.00279 -0.0499 0.9118 1.0000
1.000 0.3509 0.01027 0.00276 -0.0510 0.8740 1.0000
1.250 0.3820 0.01037 0.00275 -0.0509 0.8309 1.0000
1.500 0.4095 0.01053 0.00276 -0.0501 0.7845 1.0000
1.750 0.4354 0.01075 0.00283 -0.0490 0.7374 1.0000
2.000 0.4608 0.01100 0.00291 -0.0479 0.6896 1.0000
2.250 0.4863 0.01130 0.00301 -0.0470 0.6422 1.0000
2.500 0.5118 0.01163 0.00315 -0.0461 0.5956 1.0000
2.750 0.5373 0.01199 0.00333 -0.0454 0.5504 1.0000
3.000 0.5629 0.01236 0.00360 -0.0447 0.5070 1.0000
3.250 0.5885 0.01276 0.00385 -0.0441 0.4654 1.0000
3.500 0.6141 0.01318 0.00413 -0.0436 0.4252 1.0000
3.750 0.6398 0.01361 0.00445 -0.0431 0.3863 1.0000
4.000 0.6654 0.01407 0.00480 -0.0426 0.3491 1.0000
4.250 0.6910 0.01456 0.00526 -0.0422 0.3126 1.0000
4.500 0.7166 0.01506 0.00570 -0.0418 0.2777 1.0000
4.750 0.7420 0.01563 0.00619 -0.0415 0.2444 1.0000
5.000 0.7674 0.01621 0.00674 -0.0411 0.2129 1.0000
5.250 0.7926 0.01685 0.00735 -0.0408 0.1839 1.0000
5.500 0.8176 0.01755 0.00809 -0.0404 0.1573 1.0000
5.750 0.8423 0.01834 0.00885 -0.0400 0.1349 1.0000
6.000 0.8669 0.01914 0.00970 -0.0396 0.1131 1.0000
6.250 0.8909 0.02010 0.01067 -0.0392 0.0964 1.0000
6.500 0.9150 0.02103 0.01170 -0.0387 0.0791 1.0000
6.750 0.9383 0.02219 0.01296 -0.0381 0.0660 1.0000
7.000 0.9614 0.02337 0.01432 -0.0376 0.0528 1.0000
7.250 0.9831 0.02490 0.01598 -0.0368 0.0437 1.0000
7.500 1.0042 0.02645 0.01762 -0.0362 0.0349 1.0000
7.750 1.0254 0.02838 0.01989 -0.0352 0.0299 1.0000
8.000 1.0445 0.03020 0.02181 -0.0346 0.0247 1.0000
8.250 1.0635 0.03272 0.02474 -0.0335 0.0221 1.0000
8.500 1.0805 0.03574 0.02820 -0.0323 0.0203 1.0000
8.750 1.0953 0.03889 0.03178 -0.0313 0.0188 1.0000
9.000 1.1087 0.04136 0.03453 -0.0306 0.0170 1.0000
9.500 1.1180 0.04936 0.04337 -0.0291 0.0149 1.0000
9.750 1.1147 0.05402 0.04852 -0.0286 0.0145 1.0000
10.000 1.1043 0.05900 0.05389 -0.0287 0.0145 1.0000
10.250 1.0876 0.06389 0.05906 -0.0296 0.0145 1.0000
10.500 1.0696 0.07011 0.06548 -0.0339 0.0146 1.0000
10.750 1.0520 0.07824 0.07376 -0.0412 0.0149 1.0000
11.000 1.0342 0.08760 0.08321 -0.0488 0.0153 1.0000
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Polar data table (+)
Polar graphs
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