AG16 (ag16-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG16 (ag16-il) Reynolds number: 200,000 Max Cl/Cd: 60.33 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag16-il-200000-n5.txt Download as CSV file: xf-ag16-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG16
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5700 0.10614 0.10265 0.0140 1.0000 0.0116
-9.000 -0.5697 0.10101 0.09755 0.0115 1.0000 0.0110
-8.500 -0.5735 0.08836 0.08500 0.0046 1.0000 0.0097
-8.000 -0.5695 0.07876 0.07546 -0.0017 1.0000 0.0094
-7.750 -0.5675 0.07282 0.06956 -0.0075 1.0000 0.0093
-7.500 -0.5606 0.06503 0.06179 -0.0166 1.0000 0.0092
-7.250 -0.5485 0.05301 0.04964 -0.0303 1.0000 0.0090
-7.000 -0.5361 0.04134 0.03747 -0.0406 1.0000 0.0088
-6.750 -0.5187 0.03385 0.02931 -0.0453 1.0000 0.0089
-6.500 -0.4971 0.02883 0.02360 -0.0473 1.0000 0.0091
-6.250 -0.4728 0.02574 0.01994 -0.0480 1.0000 0.0094
-6.000 -0.4497 0.02287 0.01675 -0.0488 1.0000 0.0107
-5.750 -0.4243 0.02175 0.01543 -0.0489 1.0000 0.0121
-5.500 -0.3984 0.01978 0.01311 -0.0488 1.0000 0.0128
-5.250 -0.3723 0.01801 0.01100 -0.0485 1.0000 0.0133
-5.000 -0.3462 0.01656 0.00934 -0.0482 1.0000 0.0141
-4.750 -0.3200 0.01541 0.00802 -0.0479 1.0000 0.0150
-4.500 -0.2938 0.01415 0.00662 -0.0476 1.0000 0.0167
-4.250 -0.2676 0.01348 0.00590 -0.0474 1.0000 0.0209
-4.000 -0.2410 0.01277 0.00508 -0.0472 1.0000 0.0257
-3.750 -0.2145 0.01212 0.00439 -0.0469 1.0000 0.0362
-3.500 -0.1882 0.01152 0.00384 -0.0467 1.0000 0.0612
-3.250 -0.1620 0.01099 0.00348 -0.0466 1.0000 0.1008
-3.000 -0.1358 0.01052 0.00322 -0.0466 1.0000 0.1520
-2.750 -0.1096 0.01015 0.00303 -0.0465 1.0000 0.2046
-2.500 -0.0834 0.00987 0.00288 -0.0463 1.0000 0.2523
-2.250 -0.0469 0.00960 0.00271 -0.0483 0.9918 0.3001
-2.000 -0.0098 0.00935 0.00258 -0.0503 0.9811 0.3505
-1.750 0.0263 0.00911 0.00248 -0.0521 0.9685 0.4033
-1.500 0.0613 0.00888 0.00238 -0.0535 0.9536 0.4536
-1.250 0.0948 0.00867 0.00230 -0.0545 0.9355 0.5039
-1.000 0.1270 0.00847 0.00223 -0.0552 0.9151 0.5559
-0.750 0.1563 0.00826 0.00217 -0.0551 0.8911 0.6109
-0.500 0.1830 0.00805 0.00210 -0.0543 0.8650 0.6740
-0.250 0.2063 0.00780 0.00205 -0.0526 0.8372 0.7552
0.000 0.2307 0.00746 0.00195 -0.0507 0.8087 0.9172
0.250 0.2613 0.00752 0.00185 -0.0509 0.7778 1.0000
0.500 0.2878 0.00766 0.00182 -0.0503 0.7475 1.0000
0.750 0.3143 0.00782 0.00181 -0.0498 0.7168 1.0000
1.000 0.3410 0.00799 0.00181 -0.0493 0.6864 1.0000
1.250 0.3677 0.00817 0.00184 -0.0488 0.6561 1.0000
1.500 0.3945 0.00837 0.00190 -0.0484 0.6258 1.0000
1.750 0.4213 0.00858 0.00196 -0.0481 0.5959 1.0000
2.000 0.4482 0.00880 0.00205 -0.0477 0.5655 1.0000
2.250 0.4750 0.00903 0.00215 -0.0474 0.5349 1.0000
2.500 0.5019 0.00927 0.00227 -0.0471 0.5046 1.0000
2.750 0.5287 0.00953 0.00244 -0.0469 0.4743 1.0000
3.000 0.5554 0.00981 0.00260 -0.0466 0.4437 1.0000
3.250 0.5822 0.01009 0.00279 -0.0464 0.4129 1.0000
3.500 0.6089 0.01039 0.00300 -0.0461 0.3821 1.0000
3.750 0.6355 0.01073 0.00326 -0.0459 0.3510 1.0000
4.000 0.6620 0.01108 0.00352 -0.0457 0.3198 1.0000
4.250 0.6884 0.01145 0.00381 -0.0455 0.2886 1.0000
4.500 0.7147 0.01185 0.00413 -0.0453 0.2578 1.0000
4.750 0.7409 0.01228 0.00447 -0.0451 0.2284 1.0000
5.000 0.7670 0.01274 0.00489 -0.0449 0.2000 1.0000
5.250 0.7928 0.01323 0.00531 -0.0446 0.1720 1.0000
5.500 0.8185 0.01376 0.00577 -0.0444 0.1446 1.0000
5.750 0.8442 0.01430 0.00628 -0.0441 0.1202 1.0000
6.000 0.8694 0.01492 0.00684 -0.0439 0.0952 1.0000
6.250 0.8943 0.01560 0.00751 -0.0436 0.0736 1.0000
6.500 0.9188 0.01638 0.00823 -0.0432 0.0548 1.0000
6.750 0.9430 0.01721 0.00906 -0.0428 0.0420 1.0000
7.000 0.9668 0.01812 0.00998 -0.0423 0.0310 1.0000
7.250 0.9908 0.01896 0.01094 -0.0418 0.0239 1.0000
7.500 1.0136 0.02005 0.01214 -0.0412 0.0187 1.0000
7.750 1.0360 0.02117 0.01340 -0.0405 0.0154 1.0000
8.000 1.0563 0.02268 0.01505 -0.0397 0.0127 1.0000
8.250 1.0783 0.02374 0.01633 -0.0390 0.0107 1.0000
8.500 1.0985 0.02514 0.01790 -0.0382 0.0096 1.0000
8.750 1.1171 0.02676 0.01969 -0.0373 0.0087 1.0000
9.000 1.1313 0.02924 0.02240 -0.0360 0.0081 1.0000
9.250 1.1458 0.03166 0.02509 -0.0347 0.0078 1.0000
9.500 1.1598 0.03405 0.02780 -0.0335 0.0075 1.0000
9.750 1.1708 0.03680 0.03090 -0.0321 0.0073 1.0000
10.000 1.1779 0.03990 0.03437 -0.0306 0.0071 1.0000
10.250 1.1802 0.04330 0.03815 -0.0291 0.0070 1.0000
10.500 1.1767 0.04694 0.04215 -0.0277 0.0070 1.0000
10.750 1.1655 0.05058 0.04609 -0.0261 0.0069 1.0000
11.000 1.1512 0.05489 0.05067 -0.0263 0.0069 1.0000
11.250 1.1356 0.06024 0.05627 -0.0289 0.0069 1.0000
11.500 1.1193 0.06685 0.06311 -0.0335 0.0070 1.0000
11.750 1.1019 0.07476 0.07122 -0.0397 0.0070 1.0000
12.000 1.0832 0.08384 0.08047 -0.0466 0.0071 1.0000
12.250 1.0629 0.09379 0.09054 -0.0535 0.0072 1.0000
12.500 1.0410 0.10444 0.10129 -0.0601 0.0073 1.0000
12.750 1.0175 0.11569 0.11259 -0.0663 0.0075 1.0000
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Polar data table (+)
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