AG35 (ag35-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG35 (ag35-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.17 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag35-il-1000000.txt Download as CSV file: xf-ag35-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG35
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.4191 0.13908 0.13752 0.0035 1.0000 0.0094
-14.000 -0.4162 0.13611 0.13455 0.0025 1.0000 0.0098
-10.000 -0.6602 0.02828 0.02557 -0.0492 1.0000 0.0089
-9.750 -0.6410 0.02647 0.02358 -0.0489 1.0000 0.0092
-9.500 -0.6205 0.02508 0.02205 -0.0485 1.0000 0.0095
-9.250 -0.6029 0.02272 0.01940 -0.0477 1.0000 0.0098
-9.000 -0.5858 0.02038 0.01674 -0.0465 1.0000 0.0101
-8.750 -0.5679 0.01851 0.01459 -0.0451 1.0000 0.0104
-8.500 -0.5384 0.01679 0.01260 -0.0459 0.9979 0.0108
-8.250 -0.5056 0.01553 0.01112 -0.0472 0.9955 0.0112
-8.000 -0.4719 0.01488 0.01033 -0.0484 0.9928 0.0115
-7.750 -0.4423 0.01280 0.00801 -0.0493 0.9878 0.0124
-7.500 -0.4088 0.01236 0.00754 -0.0505 0.9835 0.0131
-7.250 -0.3786 0.01178 0.00688 -0.0509 0.9754 0.0137
-7.000 -0.3487 0.01117 0.00619 -0.0513 0.9666 0.0143
-6.750 -0.3211 0.01066 0.00560 -0.0510 0.9553 0.0148
-6.500 -0.2951 0.01028 0.00513 -0.0503 0.9424 0.0153
-6.250 -0.2701 0.00955 0.00428 -0.0495 0.9292 0.0161
-6.000 -0.2442 0.00915 0.00382 -0.0489 0.9161 0.0175
-5.750 -0.2176 0.00890 0.00351 -0.0484 0.9031 0.0186
-5.500 -0.1908 0.00866 0.00320 -0.0480 0.8900 0.0199
-5.250 -0.1637 0.00841 0.00286 -0.0475 0.8761 0.0210
-5.000 -0.1367 0.00806 0.00244 -0.0472 0.8622 0.0241
-4.750 -0.1091 0.00791 0.00223 -0.0469 0.8482 0.0267
-4.500 -0.0815 0.00768 0.00195 -0.0467 0.8332 0.0326
-4.250 -0.0538 0.00751 0.00174 -0.0464 0.8178 0.0409
-4.000 -0.0262 0.00733 0.00157 -0.0463 0.8029 0.0572
-3.750 0.0015 0.00712 0.00142 -0.0461 0.7881 0.0909
-3.500 0.0291 0.00689 0.00131 -0.0461 0.7741 0.1407
-3.250 0.0568 0.00665 0.00122 -0.0461 0.7594 0.2014
-3.000 0.0845 0.00642 0.00115 -0.0460 0.7430 0.2680
-2.750 0.1121 0.00623 0.00109 -0.0460 0.7240 0.3372
-2.500 0.1397 0.00603 0.00104 -0.0460 0.6996 0.4120
-2.250 0.1663 0.00577 0.00099 -0.0459 0.6479 0.5291
-2.000 0.1915 0.00548 0.00099 -0.0455 0.6023 0.6926
-1.750 0.2145 0.00513 0.00105 -0.0443 0.5808 0.8490
-1.500 0.2366 0.00500 0.00110 -0.0425 0.5660 0.9511
-1.250 0.2773 0.00506 0.00109 -0.0452 0.5529 0.9934
-1.000 0.3110 0.00514 0.00109 -0.0465 0.5423 1.0000
-0.750 0.3382 0.00523 0.00111 -0.0463 0.5326 1.0000
-0.500 0.3658 0.00530 0.00112 -0.0462 0.5233 1.0000
-0.250 0.3934 0.00538 0.00115 -0.0461 0.5147 1.0000
0.000 0.4211 0.00546 0.00118 -0.0461 0.5058 1.0000
0.250 0.4490 0.00553 0.00122 -0.0461 0.4971 1.0000
0.500 0.4768 0.00563 0.00126 -0.0461 0.4881 1.0000
0.750 0.5048 0.00570 0.00130 -0.0461 0.4781 1.0000
1.000 0.5329 0.00578 0.00135 -0.0462 0.4673 1.0000
1.250 0.5608 0.00587 0.00141 -0.0462 0.4545 1.0000
1.500 0.5887 0.00598 0.00147 -0.0463 0.4394 1.0000
1.750 0.6164 0.00612 0.00154 -0.0463 0.4212 1.0000
2.000 0.6440 0.00628 0.00162 -0.0463 0.4021 1.0000
2.250 0.6715 0.00645 0.00173 -0.0464 0.3809 1.0000
2.500 0.6988 0.00667 0.00185 -0.0464 0.3574 1.0000
2.750 0.7259 0.00691 0.00199 -0.0464 0.3320 1.0000
3.000 0.7530 0.00716 0.00215 -0.0465 0.3060 1.0000
3.250 0.7798 0.00744 0.00233 -0.0465 0.2804 1.0000
3.500 0.8066 0.00773 0.00252 -0.0465 0.2555 1.0000
3.750 0.8332 0.00805 0.00273 -0.0465 0.2314 1.0000
4.000 0.8599 0.00834 0.00295 -0.0465 0.2103 1.0000
4.250 0.8864 0.00866 0.00318 -0.0465 0.1901 1.0000
4.500 0.9128 0.00897 0.00342 -0.0465 0.1705 1.0000
4.750 0.9389 0.00934 0.00370 -0.0465 0.1490 1.0000
5.000 0.9650 0.00969 0.00397 -0.0464 0.1301 1.0000
5.250 0.9907 0.01009 0.00428 -0.0464 0.1110 1.0000
5.500 1.0162 0.01051 0.00461 -0.0463 0.0933 1.0000
5.750 1.0417 0.01092 0.00497 -0.0462 0.0780 1.0000
6.000 1.0668 0.01136 0.00534 -0.0461 0.0641 1.0000
6.250 1.0918 0.01182 0.00574 -0.0459 0.0518 1.0000
6.500 1.1163 0.01232 0.00618 -0.0457 0.0402 1.0000
6.750 1.1402 0.01289 0.00669 -0.0454 0.0292 1.0000
7.000 1.1638 0.01349 0.00726 -0.0451 0.0209 1.0000
7.250 1.1869 0.01415 0.00790 -0.0447 0.0157 1.0000
7.500 1.2110 0.01463 0.00842 -0.0444 0.0137 1.0000
7.750 1.2330 0.01541 0.00924 -0.0438 0.0115 1.0000
8.000 1.2566 0.01590 0.00979 -0.0435 0.0106 1.0000
8.250 1.2793 0.01649 0.01044 -0.0431 0.0097 1.0000
8.500 1.3000 0.01730 0.01130 -0.0424 0.0088 1.0000
8.750 1.3186 0.01834 0.01246 -0.0414 0.0082 1.0000
9.000 1.3398 0.01898 0.01318 -0.0408 0.0079 1.0000
9.250 1.3602 0.01969 0.01396 -0.0402 0.0075 1.0000
9.500 1.3798 0.02042 0.01476 -0.0394 0.0071 1.0000
9.750 1.3986 0.02119 0.01560 -0.0386 0.0067 1.0000
10.000 1.4148 0.02216 0.01665 -0.0375 0.0064 1.0000
10.250 1.4245 0.02365 0.01826 -0.0356 0.0060 1.0000
10.500 1.4250 0.02569 0.02047 -0.0326 0.0058 1.0000
10.750 1.4343 0.02667 0.02155 -0.0305 0.0057 1.0000
11.000 1.4409 0.02790 0.02288 -0.0285 0.0056 1.0000
11.250 1.4460 0.02934 0.02444 -0.0266 0.0055 1.0000
11.500 1.4492 0.03107 0.02628 -0.0250 0.0054 1.0000
11.750 1.4510 0.03307 0.02841 -0.0238 0.0053 1.0000
12.000 1.4513 0.03543 0.03089 -0.0230 0.0053 1.0000
12.250 1.4501 0.03816 0.03376 -0.0227 0.0052 1.0000
12.500 1.4477 0.04124 0.03698 -0.0228 0.0051 1.0000
12.750 1.4433 0.04481 0.04068 -0.0234 0.0050 1.0000
13.000 1.4377 0.04876 0.04478 -0.0245 0.0050 1.0000
13.250 1.4307 0.05327 0.04942 -0.0262 0.0049 1.0000
13.500 1.4217 0.05823 0.05452 -0.0282 0.0049 1.0000
13.750 1.4096 0.06370 0.06013 -0.0304 0.0049 1.0000
14.000 1.3961 0.06944 0.06600 -0.0328 0.0049 1.0000
14.250 1.3806 0.07556 0.07226 -0.0353 0.0048 1.0000
14.500 1.3641 0.08209 0.07892 -0.0381 0.0048 1.0000
14.750 1.3468 0.08895 0.08591 -0.0411 0.0048 1.0000
15.000 1.3291 0.09612 0.09320 -0.0443 0.0048 1.0000
15.250 1.3111 0.10353 0.10074 -0.0476 0.0048 1.0000
15.500 1.2924 0.11128 0.10862 -0.0512 0.0048 1.0000
15.750 1.2751 0.11899 0.11643 -0.0548 0.0048 1.0000
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