AG38 (ag38-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG38 (ag38-il) Reynolds number: 100,000 Max Cl/Cd: 49.13 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag38-il-100000.txt Download as CSV file: xf-ag38-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG38
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5099 0.09665 0.09175 -0.0039 1.0000 0.0796
-8.750 -0.5135 0.09346 0.08864 -0.0085 1.0000 0.0826
-8.500 -0.5138 0.08940 0.08454 -0.0226 1.0000 0.0842
-8.250 -0.5045 0.08473 0.07998 -0.0151 1.0000 0.0872
-8.000 -0.4946 0.08146 0.07673 -0.0146 1.0000 0.0916
-7.750 -0.4862 0.07708 0.07211 -0.0296 1.0000 0.0983
-7.500 -0.4773 0.07203 0.06722 -0.0264 1.0000 0.1005
-7.250 -0.4656 0.06898 0.06421 -0.0244 1.0000 0.1048
-7.000 -0.4514 0.06410 0.05909 -0.0321 1.0000 0.1140
-6.750 -0.4391 0.06103 0.05613 -0.0293 1.0000 0.1184
-6.500 -0.4228 0.05690 0.05179 -0.0329 1.0000 0.1293
-6.250 -0.4053 0.05363 0.04832 -0.0349 1.0000 0.1426
-6.000 -0.3906 0.05064 0.04546 -0.0330 1.0000 0.1498
-5.750 -0.3727 0.04759 0.04230 -0.0336 1.0000 0.1653
-5.500 -0.3544 0.04456 0.03913 -0.0344 1.0000 0.1871
-5.250 -0.3370 0.04224 0.03677 -0.0338 1.0000 0.2154
-4.750 -0.2525 0.02891 0.02111 -0.0386 1.0000 0.0827
-4.500 -0.2235 0.02579 0.01720 -0.0376 1.0000 0.0713
-4.250 -0.1977 0.02353 0.01466 -0.0368 1.0000 0.0694
-4.000 -0.1714 0.02166 0.01247 -0.0359 1.0000 0.0696
-3.750 -0.1458 0.01983 0.01052 -0.0354 1.0000 0.0743
-3.500 -0.1198 0.01851 0.00912 -0.0346 1.0000 0.0780
-3.250 -0.0934 0.01742 0.00790 -0.0337 1.0000 0.0834
-3.000 -0.0678 0.01632 0.00690 -0.0331 1.0000 0.0967
-2.750 -0.0417 0.01520 0.00595 -0.0326 1.0000 0.1175
-2.500 -0.0130 0.01120 0.00515 -0.0313 1.0000 1.0000
-2.250 0.0117 0.01127 0.00484 -0.0306 1.0000 1.0000
-2.000 0.0362 0.01136 0.00467 -0.0301 1.0000 1.0000
-1.750 0.0605 0.01148 0.00460 -0.0296 1.0000 1.0000
-1.500 0.0846 0.01163 0.00460 -0.0292 1.0000 1.0000
-1.250 0.1085 0.01181 0.00467 -0.0288 1.0000 1.0000
-1.000 0.1320 0.01205 0.00479 -0.0285 1.0000 1.0000
-0.750 0.1550 0.01234 0.00502 -0.0282 1.0000 1.0000
-0.500 0.1772 0.01271 0.00535 -0.0281 1.0000 1.0000
-0.250 0.2103 0.01313 0.00572 -0.0303 0.9954 1.0000
0.000 0.2724 0.01325 0.00582 -0.0376 0.9762 1.0000
0.250 0.3343 0.01319 0.00578 -0.0446 0.9570 1.0000
0.500 0.3881 0.01297 0.00562 -0.0494 0.9328 1.0000
0.750 0.4330 0.01270 0.00539 -0.0521 0.9041 1.0000
1.000 0.4704 0.01244 0.00516 -0.0530 0.8708 1.0000
1.250 0.5036 0.01227 0.00494 -0.0529 0.8364 1.0000
1.500 0.5325 0.01231 0.00487 -0.0520 0.8010 1.0000
1.750 0.5579 0.01252 0.00498 -0.0507 0.7636 1.0000
2.000 0.5827 0.01278 0.00515 -0.0494 0.7288 1.0000
2.250 0.6072 0.01306 0.00534 -0.0482 0.6928 1.0000
2.500 0.6317 0.01333 0.00551 -0.0469 0.6576 1.0000
2.750 0.6561 0.01367 0.00571 -0.0458 0.6224 1.0000
3.000 0.6803 0.01412 0.00604 -0.0446 0.5869 1.0000
3.250 0.7045 0.01460 0.00641 -0.0436 0.5498 1.0000
3.500 0.7285 0.01506 0.00675 -0.0426 0.5120 1.0000
3.750 0.7523 0.01544 0.00708 -0.0416 0.4698 1.0000
4.000 0.7757 0.01579 0.00738 -0.0407 0.4230 1.0000
4.250 0.7986 0.01627 0.00771 -0.0397 0.3719 1.0000
4.500 0.8209 0.01698 0.00819 -0.0388 0.3185 1.0000
4.750 0.8425 0.01790 0.00884 -0.0379 0.2657 1.0000
5.000 0.8636 0.01902 0.00973 -0.0370 0.2148 1.0000
5.250 0.8844 0.02034 0.01079 -0.0360 0.1722 1.0000
5.500 0.9054 0.02184 0.01204 -0.0351 0.1425 1.0000
5.750 0.9280 0.02320 0.01343 -0.0342 0.1209 1.0000
6.000 0.9509 0.02479 0.01500 -0.0335 0.1069 1.0000
6.250 0.9739 0.02639 0.01669 -0.0327 0.0955 1.0000
6.500 0.9977 0.02858 0.01881 -0.0322 0.0883 1.0000
6.750 1.0212 0.03042 0.02101 -0.0313 0.0820 1.0000
7.000 1.0432 0.03292 0.02347 -0.0309 0.0760 1.0000
7.250 1.0637 0.03535 0.02650 -0.0296 0.0729 1.0000
7.500 1.0820 0.03838 0.03006 -0.0282 0.0705 1.0000
7.750 1.1001 0.04099 0.03291 -0.0272 0.0673 1.0000
8.000 1.1141 0.04531 0.03734 -0.0266 0.0642 1.0000
8.250 1.1215 0.04901 0.04166 -0.0246 0.0634 1.0000
8.500 1.1255 0.05361 0.04679 -0.0228 0.0634 1.0000
8.750 1.1258 0.05879 0.05239 -0.0212 0.0636 1.0000
9.000 1.1254 0.06444 0.05836 -0.0199 0.0642 1.0000
9.250 0.9949 0.05961 0.05460 -0.0069 0.0677 1.0000
9.500 0.9484 0.06586 0.06108 -0.0060 0.0693 1.0000
9.750 0.9037 0.07381 0.06918 -0.0089 0.0710 1.0000
10.000 0.8654 0.08333 0.07874 -0.0136 0.0737 1.0000
10.250 0.8447 0.09116 0.08657 -0.0165 0.0752 1.0000
10.500 0.8318 0.09799 0.09340 -0.0183 0.0761 1.0000
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Polar data table (+)
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