AG04 (ag04-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG04 (ag04-il) Reynolds number: 50,000 Max Cl/Cd: 33.88 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag04-il-50000-n5.txt Download as CSV file: xf-ag04-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG04
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.5303 0.07323 0.06655 -0.0186 1.0000 0.0404
-6.750 -0.5189 0.06798 0.06122 -0.0220 1.0000 0.0402
-6.500 -0.5060 0.06275 0.05587 -0.0252 1.0000 0.0399
-6.250 -0.4914 0.05753 0.05048 -0.0282 1.0000 0.0396
-6.000 -0.4745 0.05224 0.04492 -0.0311 1.0000 0.0393
-5.750 -0.4553 0.04703 0.03931 -0.0336 1.0000 0.0393
-5.500 -0.4338 0.04208 0.03384 -0.0355 1.0000 0.0394
-5.250 -0.4102 0.03758 0.02862 -0.0367 1.0000 0.0400
-5.000 -0.3871 0.03424 0.02494 -0.0372 1.0000 0.0426
-4.750 -0.3625 0.03189 0.02227 -0.0374 1.0000 0.0476
-4.500 -0.3356 0.02886 0.01858 -0.0372 1.0000 0.0511
-4.250 -0.3094 0.02636 0.01572 -0.0368 1.0000 0.0552
-4.000 -0.2830 0.02471 0.01372 -0.0363 1.0000 0.0661
-3.750 -0.2573 0.02297 0.01187 -0.0356 1.0000 0.0769
-3.500 -0.2312 0.02162 0.01044 -0.0352 1.0000 0.0979
-3.250 -0.2051 0.02038 0.00916 -0.0347 1.0000 0.1290
-3.000 -0.1786 0.01927 0.00809 -0.0345 1.0000 0.1741
-2.750 -0.1528 0.01823 0.00730 -0.0342 1.0000 0.2342
-2.500 -0.1277 0.01727 0.00668 -0.0338 1.0000 0.3180
-2.250 -0.1044 0.01632 0.00618 -0.0330 1.0000 0.4373
-2.000 -0.0853 0.01524 0.00583 -0.0307 1.0000 0.6047
-1.750 -0.0489 0.01410 0.00531 -0.0306 1.0000 1.0000
-1.500 -0.0239 0.01409 0.00494 -0.0302 1.0000 1.0000
-1.250 0.0006 0.01411 0.00467 -0.0298 1.0000 1.0000
-1.000 0.0249 0.01414 0.00443 -0.0293 1.0000 1.0000
-0.750 0.0489 0.01420 0.00429 -0.0288 1.0000 1.0000
-0.500 0.0727 0.01428 0.00422 -0.0283 1.0000 1.0000
-0.250 0.0962 0.01439 0.00420 -0.0278 1.0000 1.0000
0.000 0.1195 0.01453 0.00422 -0.0274 1.0000 1.0000
0.250 0.1424 0.01471 0.00433 -0.0270 1.0000 1.0000
0.500 0.1649 0.01494 0.00451 -0.0266 1.0000 1.0000
0.750 0.2038 0.01521 0.00475 -0.0295 0.9858 1.0000
1.000 0.2542 0.01543 0.00496 -0.0343 0.9610 1.0000
1.250 0.3017 0.01559 0.00515 -0.0381 0.9338 1.0000
1.500 0.3445 0.01572 0.00532 -0.0408 0.9030 1.0000
1.750 0.3824 0.01584 0.00549 -0.0421 0.8691 1.0000
2.000 0.4154 0.01596 0.00562 -0.0423 0.8324 1.0000
2.250 0.4443 0.01612 0.00576 -0.0415 0.7938 1.0000
2.500 0.4708 0.01632 0.00591 -0.0403 0.7545 1.0000
2.750 0.4957 0.01656 0.00615 -0.0387 0.7143 1.0000
3.000 0.5199 0.01686 0.00636 -0.0371 0.6734 1.0000
3.250 0.5438 0.01720 0.00662 -0.0356 0.6318 1.0000
3.500 0.5676 0.01759 0.00692 -0.0341 0.5897 1.0000
3.750 0.5914 0.01802 0.00728 -0.0328 0.5476 1.0000
4.000 0.6152 0.01851 0.00774 -0.0316 0.5059 1.0000
4.250 0.6391 0.01905 0.00821 -0.0305 0.4650 1.0000
4.500 0.6629 0.01964 0.00873 -0.0295 0.4254 1.0000
4.750 0.6870 0.02029 0.00933 -0.0287 0.3868 1.0000
5.000 0.7114 0.02100 0.01008 -0.0280 0.3489 1.0000
5.250 0.7354 0.02177 0.01084 -0.0274 0.3127 1.0000
5.500 0.7592 0.02260 0.01167 -0.0267 0.2778 1.0000
5.750 0.7827 0.02351 0.01259 -0.0261 0.2442 1.0000
6.000 0.8058 0.02451 0.01361 -0.0255 0.2115 1.0000
6.250 0.8283 0.02562 0.01479 -0.0248 0.1813 1.0000
6.500 0.8504 0.02687 0.01606 -0.0242 0.1535 1.0000
6.750 0.8724 0.02832 0.01761 -0.0234 0.1293 1.0000
7.000 0.8935 0.02987 0.01923 -0.0227 0.1078 1.0000
7.250 0.9146 0.03174 0.02126 -0.0218 0.0924 1.0000
7.500 0.9347 0.03361 0.02329 -0.0210 0.0784 1.0000
7.750 0.9546 0.03595 0.02586 -0.0201 0.0688 1.0000
8.000 0.9729 0.03828 0.02826 -0.0192 0.0614 1.0000
8.250 0.9904 0.04099 0.03159 -0.0183 0.0535 1.0000
8.500 1.0062 0.04394 0.03465 -0.0175 0.0497 1.0000
8.750 1.0176 0.04823 0.03964 -0.0165 0.0468 1.0000
9.000 1.0244 0.05232 0.04431 -0.0158 0.0434 1.0000
9.250 1.0306 0.05555 0.04781 -0.0153 0.0402 1.0000
9.500 1.0342 0.05915 0.05158 -0.0148 0.0384 1.0000
9.750 1.0293 0.06400 0.05671 -0.0147 0.0378 1.0000
10.000 1.0171 0.06911 0.06217 -0.0153 0.0377 1.0000
10.250 1.0002 0.07410 0.06737 -0.0163 0.0377 1.0000
10.500 0.9830 0.07985 0.07327 -0.0195 0.0379 1.0000
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Polar data table (+)
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