AG14 (ag14-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG14 (ag14-il) Reynolds number: 200,000 Max Cl/Cd: 59.38 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag14-il-200000-n5.txt Download as CSV file: xf-ag14-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5595 0.11512 0.11157 0.0184 1.0000 0.0163
-8.750 -0.5541 0.11129 0.10776 0.0167 1.0000 0.0163
-8.500 -0.5487 0.10745 0.10394 0.0149 1.0000 0.0163
-8.250 -0.5432 0.10359 0.10011 0.0130 1.0000 0.0163
-8.000 -0.5378 0.09971 0.09627 0.0109 1.0000 0.0163
-7.750 -0.5322 0.09580 0.09238 0.0087 1.0000 0.0163
-6.750 -0.5051 0.07812 0.07479 -0.0011 1.0000 0.0140
-6.500 -0.4910 0.07289 0.06957 -0.0068 1.0000 0.0128
-6.250 -0.4725 0.06657 0.06322 -0.0143 1.0000 0.0117
-6.000 -0.4462 0.05705 0.05359 -0.0254 1.0000 0.0105
-5.750 -0.4180 0.04897 0.04532 -0.0332 1.0000 0.0102
-5.500 -0.3968 0.04643 0.04269 -0.0357 1.0000 0.0114
-5.250 -0.3702 0.04201 0.03808 -0.0393 1.0000 0.0131
-5.000 -0.3409 0.03587 0.03158 -0.0431 1.0000 0.0138
-4.750 -0.3119 0.02993 0.02514 -0.0457 1.0000 0.0132
-4.500 -0.2827 0.02494 0.01953 -0.0472 1.0000 0.0128
-4.250 -0.2538 0.02123 0.01521 -0.0478 1.0000 0.0127
-4.000 -0.2255 0.01858 0.01200 -0.0478 1.0000 0.0127
-3.750 -0.1977 0.01663 0.00966 -0.0476 1.0000 0.0131
-3.500 -0.1704 0.01510 0.00786 -0.0473 1.0000 0.0138
-3.250 -0.1433 0.01389 0.00647 -0.0469 1.0000 0.0150
-3.000 -0.1165 0.01290 0.00536 -0.0466 1.0000 0.0175
-2.750 -0.0899 0.01219 0.00462 -0.0463 1.0000 0.0214
-2.500 -0.0628 0.01153 0.00382 -0.0460 1.0000 0.0252
-2.250 -0.0359 0.01094 0.00321 -0.0457 1.0000 0.0366
-2.000 -0.0089 0.01041 0.00277 -0.0455 1.0000 0.0641
-1.750 0.0177 0.00991 0.00253 -0.0455 1.0000 0.1231
-1.500 0.0444 0.00947 0.00238 -0.0455 1.0000 0.2035
-1.250 0.0721 0.00903 0.00227 -0.0457 0.9989 0.3053
-1.000 0.1095 0.00849 0.00219 -0.0480 0.9858 0.4485
-0.750 0.1438 0.00779 0.00214 -0.0494 0.9692 0.6367
-0.500 0.1769 0.00697 0.00198 -0.0494 0.9461 1.0000
-0.250 0.2135 0.00699 0.00185 -0.0509 0.9164 1.0000
0.000 0.2464 0.00703 0.00173 -0.0515 0.8791 1.0000
0.250 0.2749 0.00712 0.00164 -0.0511 0.8370 1.0000
0.500 0.3009 0.00727 0.00159 -0.0502 0.7929 1.0000
0.750 0.3263 0.00747 0.00155 -0.0492 0.7482 1.0000
1.000 0.3519 0.00769 0.00155 -0.0483 0.7035 1.0000
1.250 0.3776 0.00794 0.00157 -0.0476 0.6588 1.0000
1.500 0.4035 0.00821 0.00161 -0.0470 0.6149 1.0000
1.750 0.4296 0.00849 0.00170 -0.0464 0.5723 1.0000
2.000 0.4559 0.00877 0.00179 -0.0460 0.5312 1.0000
2.250 0.4823 0.00906 0.00190 -0.0456 0.4919 1.0000
2.500 0.5089 0.00935 0.00203 -0.0453 0.4546 1.0000
2.750 0.5354 0.00966 0.00218 -0.0450 0.4186 1.0000
3.000 0.5620 0.00997 0.00240 -0.0447 0.3834 1.0000
3.250 0.5885 0.01030 0.00260 -0.0445 0.3504 1.0000
3.500 0.6151 0.01063 0.00282 -0.0443 0.3177 1.0000
3.750 0.6416 0.01098 0.00307 -0.0440 0.2865 1.0000
4.000 0.6680 0.01135 0.00335 -0.0438 0.2566 1.0000
4.250 0.6944 0.01173 0.00369 -0.0436 0.2278 1.0000
4.500 0.7208 0.01214 0.00403 -0.0434 0.2006 1.0000
4.750 0.7470 0.01258 0.00441 -0.0432 0.1741 1.0000
5.000 0.7731 0.01303 0.00482 -0.0430 0.1510 1.0000
5.250 0.7991 0.01351 0.00527 -0.0427 0.1285 1.0000
5.500 0.8249 0.01405 0.00581 -0.0425 0.1097 1.0000
5.750 0.8507 0.01458 0.00635 -0.0422 0.0924 1.0000
6.000 0.8762 0.01515 0.00694 -0.0419 0.0771 1.0000
6.250 0.9016 0.01577 0.00759 -0.0416 0.0637 1.0000
6.500 0.9267 0.01644 0.00830 -0.0412 0.0513 1.0000
6.750 0.9515 0.01718 0.00910 -0.0409 0.0405 1.0000
7.000 0.9758 0.01804 0.01007 -0.0404 0.0313 1.0000
7.250 0.9994 0.01905 0.01113 -0.0400 0.0233 1.0000
7.500 1.0231 0.02005 0.01229 -0.0394 0.0184 1.0000
7.750 1.0442 0.02167 0.01406 -0.0386 0.0150 1.0000
8.000 1.0673 0.02269 0.01527 -0.0380 0.0123 1.0000
8.250 1.0889 0.02399 0.01674 -0.0374 0.0106 1.0000
8.500 1.1061 0.02636 0.01935 -0.0364 0.0094 1.0000
8.750 1.1240 0.02855 0.02184 -0.0353 0.0088 1.0000
9.000 1.1409 0.03092 0.02461 -0.0342 0.0084 1.0000
9.250 1.1553 0.03372 0.02781 -0.0331 0.0080 1.0000
9.500 1.1663 0.03698 0.03150 -0.0319 0.0077 1.0000
9.750 1.1729 0.04072 0.03569 -0.0307 0.0075 1.0000
10.000 1.1746 0.04470 0.04012 -0.0297 0.0074 1.0000
10.250 1.1718 0.04871 0.04450 -0.0289 0.0071 1.0000
10.500 1.1620 0.05278 0.04889 -0.0283 0.0070 1.0000
10.750 1.1453 0.05763 0.05400 -0.0296 0.0070 1.0000
11.000 1.1253 0.06497 0.06159 -0.0354 0.0071 1.0000
11.250 1.1028 0.07555 0.07238 -0.0450 0.0074 1.0000
11.500 1.0799 0.08727 0.08423 -0.0541 0.0077 1.0000
11.750 1.0559 0.09896 0.09599 -0.0615 0.0080 1.0000
12.000 1.0301 0.11083 0.10781 -0.0678 0.0082 1.0000
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Polar data table (+)
Polar graphs
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