AG19 (ag19-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG19 (ag19-il) Reynolds number: 200,000 Max Cl/Cd: 66.09 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag19-il-200000.txt Download as CSV file: xf-ag19-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG19
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5241 0.10298 0.09958 0.0053 1.0000 0.0272
-7.750 -0.5208 0.09779 0.09447 0.0023 1.0000 0.0274
-7.500 -0.5191 0.09234 0.08902 0.0042 1.0000 0.0285
-7.250 -0.5106 0.08888 0.08558 0.0042 1.0000 0.0294
-7.000 -0.5006 0.08530 0.08202 0.0021 1.0000 0.0304
-6.750 -0.4890 0.08147 0.07820 -0.0013 1.0000 0.0316
-6.500 -0.4751 0.07732 0.07406 -0.0058 1.0000 0.0330
-6.250 -0.4580 0.07276 0.06950 -0.0116 1.0000 0.0348
-6.000 -0.4326 0.06729 0.06399 -0.0207 1.0000 0.0374
-5.750 -0.3900 0.06090 0.05731 -0.0346 1.0000 0.0391
-5.500 -0.3758 0.05343 0.04979 -0.0387 1.0000 0.0403
-5.250 -0.3626 0.05070 0.04713 -0.0380 1.0000 0.0422
-5.000 -0.3395 0.04759 0.04390 -0.0402 1.0000 0.0483
-4.750 -0.3087 0.04164 0.03763 -0.0458 1.0000 0.0546
-4.500 -0.2862 0.03889 0.03482 -0.0466 1.0000 0.0587
-4.250 -0.2542 0.03417 0.02960 -0.0502 1.0000 0.0674
-4.000 -0.2308 0.03168 0.02710 -0.0505 1.0000 0.0714
-3.750 -0.2024 0.02858 0.02363 -0.0518 1.0000 0.0819
-3.500 -0.1609 0.02007 0.01385 -0.0520 1.0000 0.0334
-3.250 -0.1307 0.01691 0.01000 -0.0514 1.0000 0.0295
-3.000 -0.1031 0.01511 0.00792 -0.0509 1.0000 0.0297
-2.750 -0.0762 0.01377 0.00646 -0.0504 1.0000 0.0322
-2.500 -0.0498 0.01329 0.00583 -0.0498 1.0000 0.0391
-2.250 -0.0224 0.01172 0.00430 -0.0496 1.0000 0.0476
-2.000 0.0053 0.01080 0.00344 -0.0495 1.0000 0.0747
-1.750 0.0337 0.00960 0.00287 -0.0499 1.0000 0.2093
-1.500 0.0607 0.00869 0.00278 -0.0503 1.0000 0.4314
-1.250 0.0833 0.00760 0.00271 -0.0491 1.0000 0.7182
-1.000 0.1061 0.00711 0.00255 -0.0474 1.0000 1.0000
-0.750 0.1328 0.00719 0.00248 -0.0473 1.0000 1.0000
-0.500 0.1593 0.00729 0.00246 -0.0472 1.0000 1.0000
-0.250 0.1855 0.00742 0.00250 -0.0472 1.0000 1.0000
0.000 0.2274 0.00751 0.00248 -0.0503 0.9908 1.0000
0.250 0.2747 0.00753 0.00244 -0.0544 0.9770 1.0000
0.500 0.3180 0.00751 0.00238 -0.0573 0.9600 1.0000
0.750 0.3573 0.00749 0.00232 -0.0593 0.9395 1.0000
1.000 0.3907 0.00747 0.00226 -0.0599 0.9141 1.0000
1.250 0.4183 0.00750 0.00223 -0.0591 0.8838 1.0000
1.500 0.4434 0.00758 0.00222 -0.0577 0.8508 1.0000
1.750 0.4678 0.00770 0.00224 -0.0563 0.8159 1.0000
2.000 0.4922 0.00787 0.00227 -0.0549 0.7781 1.0000
2.250 0.5168 0.00808 0.00232 -0.0537 0.7371 1.0000
2.500 0.5416 0.00832 0.00239 -0.0526 0.6921 1.0000
2.750 0.5666 0.00860 0.00248 -0.0517 0.6423 1.0000
3.000 0.5915 0.00895 0.00264 -0.0508 0.5867 1.0000
3.250 0.6165 0.00935 0.00280 -0.0500 0.5276 1.0000
3.500 0.6415 0.00981 0.00301 -0.0494 0.4694 1.0000
3.750 0.6668 0.01030 0.00327 -0.0488 0.4158 1.0000
4.000 0.6921 0.01081 0.00358 -0.0484 0.3681 1.0000
4.250 0.7177 0.01132 0.00396 -0.0481 0.3253 1.0000
4.500 0.7433 0.01184 0.00434 -0.0477 0.2861 1.0000
4.750 0.7690 0.01236 0.00475 -0.0474 0.2488 1.0000
5.000 0.7944 0.01293 0.00521 -0.0471 0.2152 1.0000
5.250 0.8199 0.01353 0.00572 -0.0468 0.1828 1.0000
5.500 0.8450 0.01420 0.00636 -0.0464 0.1555 1.0000
5.750 0.8700 0.01492 0.00702 -0.0460 0.1312 1.0000
6.000 0.8943 0.01580 0.00779 -0.0456 0.1108 1.0000
6.250 0.9193 0.01657 0.00863 -0.0451 0.0930 1.0000
6.500 0.9437 0.01741 0.00949 -0.0447 0.0767 1.0000
6.750 0.9675 0.01845 0.01057 -0.0441 0.0630 1.0000
7.000 0.9909 0.01958 0.01176 -0.0434 0.0506 1.0000
7.250 1.0138 0.02093 0.01327 -0.0426 0.0405 1.0000
7.500 1.0350 0.02292 0.01540 -0.0416 0.0333 1.0000
7.750 1.0572 0.02441 0.01702 -0.0408 0.0278 1.0000
8.000 1.0767 0.02707 0.01998 -0.0397 0.0237 1.0000
8.250 1.0967 0.02967 0.02296 -0.0384 0.0215 1.0000
8.500 1.1143 0.03272 0.02643 -0.0371 0.0201 1.0000
8.750 1.1284 0.03638 0.03056 -0.0358 0.0194 1.0000
9.000 1.1373 0.04094 0.03566 -0.0343 0.0192 1.0000
9.250 1.1434 0.04497 0.04012 -0.0331 0.0186 1.0000
9.500 1.1473 0.04849 0.04387 -0.0323 0.0175 1.0000
9.750 1.1389 0.05381 0.04957 -0.0314 0.0171 1.0000
10.000 1.1260 0.05885 0.05494 -0.0308 0.0170 1.0000
10.250 1.1097 0.06305 0.05938 -0.0304 0.0170 1.0000
10.500 1.0943 0.06780 0.06435 -0.0326 0.0172 1.0000
10.750 1.0180 0.09452 0.09160 -0.0562 0.0225 1.0000
11.000 0.9960 0.10668 0.10371 -0.0633 0.0234 1.0000
11.250 0.9814 0.11550 0.11248 -0.0677 0.0240 1.0000
11.500 0.9699 0.12315 0.12009 -0.0711 0.0247 1.0000
11.750 0.9466 0.13849 0.13535 -0.0786 0.0318 1.0000
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Polar data table (+)
Polar graphs
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