AG03 (flat aft bottom) (ag03-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG03 (flat aft bottom) (ag03-il) Reynolds number: 100,000 Max Cl/Cd: 46.71 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag03-il-100000.txt Download as CSV file: xf-ag03-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG03 (flat aft bottom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5488 0.11352 0.10870 0.0107 1.0000 0.0640
-8.500 -0.5519 0.11117 0.10643 0.0051 1.0000 0.0645
-8.250 -0.5527 0.10817 0.10349 -0.0019 1.0000 0.0648
-8.000 -0.5329 0.10085 0.09615 0.0079 1.0000 0.0677
-7.750 -0.5256 0.09729 0.09262 0.0074 1.0000 0.0703
-7.500 -0.5214 0.09383 0.08920 0.0053 1.0000 0.0730
-7.250 -0.5173 0.09019 0.08561 -0.0007 1.0000 0.0761
-7.000 -0.5065 0.08631 0.08160 -0.0183 1.0000 0.0781
-6.750 -0.4996 0.08080 0.07625 -0.0115 1.0000 0.0800
-6.500 -0.4886 0.07729 0.07277 -0.0101 1.0000 0.0832
-6.250 -0.4742 0.07317 0.06862 -0.0149 1.0000 0.0885
-6.000 -0.4572 0.06788 0.06318 -0.0231 1.0000 0.0931
-5.750 -0.4447 0.06447 0.05985 -0.0211 1.0000 0.0968
-5.500 -0.4225 0.05993 0.05501 -0.0285 1.0000 0.1064
-5.250 -0.4086 0.05637 0.05158 -0.0267 1.0000 0.1103
-5.000 -0.3870 0.05236 0.04734 -0.0303 1.0000 0.1212
-4.500 -0.3479 0.04572 0.04055 -0.0313 1.0000 0.1403
-4.250 -0.3265 0.04251 0.03720 -0.0322 1.0000 0.1539
-4.000 -0.3043 0.03963 0.03409 -0.0332 1.0000 0.1765
-3.750 -0.2833 0.03666 0.03108 -0.0329 1.0000 0.1921
-3.500 -0.2247 0.02547 0.01763 -0.0343 1.0000 0.0490
-3.250 -0.1986 0.02292 0.01464 -0.0335 1.0000 0.0484
-3.000 -0.1718 0.02134 0.01257 -0.0325 1.0000 0.0514
-2.750 -0.1463 0.01897 0.01006 -0.0318 1.0000 0.0555
-2.500 -0.1200 0.01743 0.00837 -0.0308 1.0000 0.0626
-2.250 -0.0946 0.01586 0.00687 -0.0299 1.0000 0.0837
-2.000 -0.0694 0.01444 0.00571 -0.0292 1.0000 0.1465
-1.750 -0.0453 0.01202 0.00474 -0.0289 1.0000 0.3992
-1.500 -0.0112 0.01028 0.00431 -0.0282 1.0000 1.0000
-1.250 0.0123 0.01033 0.00405 -0.0274 1.0000 1.0000
-1.000 0.0356 0.01040 0.00386 -0.0267 1.0000 1.0000
-0.750 0.0589 0.01050 0.00376 -0.0261 1.0000 1.0000
-0.500 0.0821 0.01063 0.00374 -0.0256 1.0000 1.0000
-0.250 0.1051 0.01080 0.00379 -0.0252 1.0000 1.0000
0.000 0.1279 0.01102 0.00389 -0.0249 1.0000 1.0000
0.250 0.1503 0.01130 0.00408 -0.0247 1.0000 1.0000
0.500 0.1723 0.01166 0.00438 -0.0246 1.0000 1.0000
0.750 0.2330 0.01190 0.00456 -0.0318 0.9827 1.0000
1.000 0.2911 0.01198 0.00463 -0.0380 0.9618 1.0000
1.250 0.3478 0.01194 0.00461 -0.0435 0.9416 1.0000
1.500 0.3913 0.01187 0.00457 -0.0459 0.9148 1.0000
1.750 0.4256 0.01181 0.00454 -0.0461 0.8845 1.0000
2.000 0.4527 0.01181 0.00451 -0.0448 0.8507 1.0000
2.250 0.4774 0.01184 0.00448 -0.0429 0.8168 1.0000
2.500 0.5004 0.01196 0.00451 -0.0409 0.7789 1.0000
2.750 0.5234 0.01212 0.00457 -0.0389 0.7402 1.0000
3.000 0.5466 0.01235 0.00471 -0.0372 0.7000 1.0000
3.250 0.5700 0.01262 0.00484 -0.0356 0.6581 1.0000
3.500 0.5936 0.01295 0.00502 -0.0341 0.6149 1.0000
3.750 0.6174 0.01332 0.00523 -0.0328 0.5711 1.0000
4.000 0.6412 0.01376 0.00554 -0.0316 0.5273 1.0000
4.250 0.6651 0.01424 0.00585 -0.0306 0.4833 1.0000
4.500 0.6891 0.01477 0.00623 -0.0297 0.4396 1.0000
4.750 0.7130 0.01535 0.00667 -0.0288 0.3977 1.0000
5.000 0.7368 0.01600 0.00720 -0.0281 0.3579 1.0000
5.250 0.7605 0.01669 0.00775 -0.0273 0.3197 1.0000
5.500 0.7843 0.01743 0.00841 -0.0266 0.2820 1.0000
5.750 0.8077 0.01830 0.00915 -0.0260 0.2480 1.0000
6.000 0.8311 0.01920 0.00999 -0.0253 0.2146 1.0000
6.250 0.8543 0.02026 0.01102 -0.0246 0.1860 1.0000
6.500 0.8776 0.02145 0.01219 -0.0239 0.1616 1.0000
6.750 0.9005 0.02273 0.01334 -0.0233 0.1413 1.0000
7.000 0.9243 0.02423 0.01498 -0.0225 0.1253 1.0000
7.250 0.9472 0.02565 0.01652 -0.0218 0.1103 1.0000
7.500 0.9703 0.02751 0.01849 -0.0210 0.0990 1.0000
7.750 0.9928 0.02963 0.02064 -0.0204 0.0889 1.0000
8.000 1.0142 0.03125 0.02265 -0.0194 0.0791 1.0000
8.250 1.0337 0.03449 0.02638 -0.0182 0.0730 1.0000
8.500 1.0529 0.03689 0.02876 -0.0177 0.0648 1.0000
8.750 1.0654 0.04069 0.03342 -0.0160 0.0613 1.0000
9.000 1.0753 0.04475 0.03811 -0.0145 0.0579 1.0000
9.250 1.0880 0.04830 0.04152 -0.0141 0.0523 1.0000
9.500 1.0872 0.05275 0.04674 -0.0125 0.0511 1.0000
9.750 1.0807 0.05818 0.05270 -0.0115 0.0508 1.0000
10.000 1.0692 0.06363 0.05854 -0.0109 0.0509 1.0000
10.250 1.0538 0.06895 0.06412 -0.0109 0.0512 1.0000
10.500 1.0353 0.07392 0.06925 -0.0112 0.0516 1.0000
10.750 1.0177 0.07959 0.07502 -0.0132 0.0521 1.0000
11.000 0.8076 0.09521 0.09091 -0.0218 0.0749 1.0000
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Polar data table (+)
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