AG38 (ag38-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG38 (ag38-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.95 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag38-il-1000000.txt Download as CSV file: xf-ag38-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5447 0.09318 0.09157 -0.0013 1.0000 0.0094
-9.500 -0.5418 0.08965 0.08806 -0.0031 1.0000 0.0095
-9.250 -0.5388 0.08615 0.08457 -0.0051 1.0000 0.0096
-9.000 -0.5367 0.08261 0.08105 -0.0075 1.0000 0.0097
-8.750 -0.5300 0.07858 0.07703 -0.0117 1.0000 0.0098
-8.500 -0.5206 0.07419 0.07264 -0.0166 1.0000 0.0100
-8.250 -0.5095 0.06951 0.06793 -0.0217 1.0000 0.0102
-8.000 -0.4971 0.06456 0.06294 -0.0265 1.0000 0.0105
-7.750 -0.4840 0.05946 0.05779 -0.0307 1.0000 0.0108
-7.500 -0.4713 0.05432 0.05255 -0.0338 1.0000 0.0111
-7.250 -0.4578 0.04908 0.04719 -0.0359 1.0000 0.0116
-7.000 -0.4384 0.04309 0.04100 -0.0370 1.0000 0.0126
-6.750 -0.4220 0.03828 0.03597 -0.0369 1.0000 0.0127
-6.500 -0.4060 0.03346 0.03086 -0.0366 1.0000 0.0128
-6.250 -0.3888 0.02906 0.02612 -0.0360 1.0000 0.0128
-6.000 -0.3669 0.01902 0.01525 -0.0375 0.9992 0.0110
-5.750 -0.3348 0.01504 0.01068 -0.0384 0.9982 0.0109
-5.500 -0.3016 0.01314 0.00848 -0.0395 0.9970 0.0111
-5.250 -0.2673 0.01184 0.00698 -0.0408 0.9958 0.0114
-5.000 -0.2321 0.01110 0.00614 -0.0423 0.9947 0.0120
-4.750 -0.1982 0.01037 0.00531 -0.0434 0.9928 0.0125
-4.500 -0.1646 0.00930 0.00413 -0.0446 0.9906 0.0133
-4.250 -0.1294 0.00865 0.00345 -0.0462 0.9884 0.0145
-4.000 -0.0930 0.00827 0.00306 -0.0480 0.9861 0.0158
-3.750 -0.0574 0.00794 0.00271 -0.0496 0.9833 0.0171
-3.500 -0.0276 0.00752 0.00223 -0.0498 0.9763 0.0196
-3.250 0.0038 0.00729 0.00200 -0.0504 0.9697 0.0226
-3.000 0.0308 0.00706 0.00174 -0.0499 0.9588 0.0263
-2.750 0.0573 0.00685 0.00154 -0.0493 0.9459 0.0356
-2.500 0.0832 0.00655 0.00138 -0.0487 0.9299 0.0812
-2.250 0.1088 0.00618 0.00126 -0.0481 0.9063 0.1724
-2.000 0.1324 0.00583 0.00112 -0.0471 0.8457 0.3061
-1.750 0.1580 0.00547 0.00108 -0.0468 0.8052 0.4721
-1.500 0.1835 0.00492 0.00108 -0.0465 0.7726 0.6976
-1.250 0.2020 0.00438 0.00112 -0.0440 0.7419 0.9176
-1.000 0.2363 0.00437 0.00102 -0.0451 0.6997 1.0000
-0.750 0.2629 0.00464 0.00100 -0.0448 0.6301 1.0000
-0.500 0.2901 0.00486 0.00102 -0.0447 0.5937 1.0000
0.000 0.3458 0.00515 0.00108 -0.0447 0.5524 1.0000
0.250 0.3739 0.00526 0.00111 -0.0447 0.5364 1.0000
0.500 0.4020 0.00537 0.00115 -0.0447 0.5213 1.0000
0.750 0.4301 0.00548 0.00119 -0.0448 0.5063 1.0000
1.000 0.4582 0.00559 0.00124 -0.0448 0.4903 1.0000
1.250 0.4863 0.00571 0.00130 -0.0449 0.4725 1.0000
1.500 0.5143 0.00584 0.00135 -0.0449 0.4507 1.0000
1.750 0.5421 0.00601 0.00141 -0.0450 0.4216 1.0000
2.000 0.5696 0.00624 0.00151 -0.0450 0.3861 1.0000
2.250 0.5969 0.00652 0.00163 -0.0451 0.3477 1.0000
2.500 0.6241 0.00680 0.00176 -0.0451 0.3120 1.0000
2.750 0.6514 0.00709 0.00191 -0.0451 0.2766 1.0000
3.000 0.6786 0.00738 0.00208 -0.0452 0.2466 1.0000
3.250 0.7057 0.00768 0.00226 -0.0452 0.2161 1.0000
3.500 0.7327 0.00801 0.00245 -0.0452 0.1868 1.0000
3.750 0.7596 0.00834 0.00266 -0.0452 0.1586 1.0000
4.000 0.7864 0.00868 0.00289 -0.0453 0.1336 1.0000
4.250 0.8132 0.00902 0.00314 -0.0453 0.1114 1.0000
4.500 0.8397 0.00941 0.00341 -0.0452 0.0890 1.0000
4.750 0.8662 0.00978 0.00371 -0.0452 0.0707 1.0000
5.000 0.8925 0.01017 0.00402 -0.0451 0.0562 1.0000
5.250 0.9189 0.01053 0.00435 -0.0451 0.0464 1.0000
5.500 0.9453 0.01090 0.00470 -0.0450 0.0392 1.0000
5.750 0.9712 0.01134 0.00512 -0.0449 0.0328 1.0000
6.000 0.9975 0.01168 0.00550 -0.0448 0.0299 1.0000
6.250 1.0236 0.01204 0.00588 -0.0447 0.0272 1.0000
6.500 1.0481 0.01271 0.00659 -0.0443 0.0234 1.0000
6.750 1.0741 0.01304 0.00696 -0.0442 0.0224 1.0000
7.000 1.0999 0.01340 0.00737 -0.0440 0.0210 1.0000
7.250 1.1251 0.01382 0.00784 -0.0439 0.0197 1.0000
7.500 1.1493 0.01444 0.00848 -0.0435 0.0181 1.0000
7.750 1.1713 0.01539 0.00955 -0.0428 0.0166 1.0000
8.000 1.1966 0.01572 0.00994 -0.0427 0.0160 1.0000
8.250 1.2208 0.01621 0.01050 -0.0423 0.0152 1.0000
8.500 1.2446 0.01674 0.01109 -0.0420 0.0144 1.0000
8.750 1.2680 0.01730 0.01169 -0.0416 0.0136 1.0000
9.000 1.2888 0.01821 0.01267 -0.0409 0.0127 1.0000
9.250 1.3062 0.01960 0.01421 -0.0396 0.0118 1.0000
9.500 1.3296 0.02003 0.01472 -0.0393 0.0115 1.0000
9.750 1.3513 0.02068 0.01546 -0.0387 0.0110 1.0000
10.000 1.3722 0.02140 0.01626 -0.0381 0.0104 1.0000
10.250 1.3927 0.02211 0.01705 -0.0374 0.0100 1.0000
10.500 1.4126 0.02284 0.01784 -0.0367 0.0095 1.0000
10.750 1.4293 0.02390 0.01898 -0.0355 0.0090 1.0000
11.000 1.4295 0.02677 0.02212 -0.0324 0.0084 1.0000
11.250 1.4482 0.02739 0.02282 -0.0316 0.0082 1.0000
11.500 1.4651 0.02814 0.02368 -0.0305 0.0080 1.0000
11.750 1.4791 0.02909 0.02475 -0.0292 0.0077 1.0000
12.000 1.4885 0.03029 0.02606 -0.0273 0.0074 1.0000
12.250 1.4928 0.03153 0.02742 -0.0246 0.0072 1.0000
12.500 1.4962 0.03293 0.02893 -0.0223 0.0070 1.0000
12.750 1.4990 0.03451 0.03062 -0.0203 0.0068 1.0000
13.000 1.5018 0.03626 0.03247 -0.0189 0.0066 1.0000
13.250 1.5024 0.03842 0.03474 -0.0180 0.0065 1.0000
13.500 1.4993 0.04134 0.03777 -0.0179 0.0063 1.0000
13.750 1.4916 0.04530 0.04188 -0.0189 0.0062 1.0000
14.000 1.4784 0.05065 0.04740 -0.0212 0.0061 1.0000
14.250 1.4620 0.05735 0.05428 -0.0250 0.0060 1.0000
14.500 1.4425 0.06486 0.06196 -0.0293 0.0060 1.0000
14.750 1.4215 0.07270 0.06997 -0.0336 0.0060 1.0000
15.000 1.3977 0.08117 0.07859 -0.0381 0.0060 1.0000
15.250 1.3724 0.09006 0.08762 -0.0425 0.0061 1.0000
15.500 1.3439 0.09970 0.09741 -0.0472 0.0062 1.0000
15.750 1.3088 0.11085 0.10872 -0.0526 0.0063 1.0000
16.000 1.2673 0.12394 0.12199 -0.0591 0.0065 1.0000
16.250 1.2126 0.14080 0.13906 -0.0676 0.0068 1.0000
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