AG37 (ag37-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG37 (ag37-il) Reynolds number: 500,000 Max Cl/Cd: 78.64 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag37-il-500000-n5.txt Download as CSV file: xf-ag37-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG37
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5293 0.08850 0.08624 -0.0045 1.0000 0.0079
-9.500 -0.5295 0.08402 0.08179 -0.0074 1.0000 0.0078
-9.250 -0.5315 0.07929 0.07709 -0.0110 1.0000 0.0077
-9.000 -0.5284 0.07326 0.07107 -0.0178 1.0000 0.0076
-8.750 -0.5226 0.06626 0.06404 -0.0253 1.0000 0.0074
-8.500 -0.5152 0.05834 0.05602 -0.0324 1.0000 0.0074
-8.250 -0.5076 0.04935 0.04683 -0.0381 1.0000 0.0073
-8.000 -0.5020 0.03867 0.03574 -0.0414 1.0000 0.0074
-7.750 -0.5044 0.02173 0.01730 -0.0417 1.0000 0.0080
-7.500 -0.4844 0.01874 0.01377 -0.0407 1.0000 0.0083
-7.250 -0.4620 0.01719 0.01190 -0.0398 1.0000 0.0087
-7.000 -0.4384 0.01583 0.01030 -0.0392 0.9997 0.0091
-6.750 -0.4055 0.01507 0.00945 -0.0404 0.9973 0.0096
-6.500 -0.3725 0.01426 0.00851 -0.0416 0.9950 0.0101
-6.250 -0.3407 0.01339 0.00749 -0.0425 0.9924 0.0106
-6.000 -0.3083 0.01259 0.00656 -0.0434 0.9891 0.0112
-5.750 -0.2747 0.01191 0.00577 -0.0446 0.9858 0.0119
-5.500 -0.2419 0.01123 0.00501 -0.0457 0.9822 0.0126
-5.250 -0.2109 0.01072 0.00446 -0.0463 0.9758 0.0136
-5.000 -0.1770 0.01039 0.00412 -0.0476 0.9699 0.0151
-4.750 -0.1467 0.01006 0.00374 -0.0479 0.9601 0.0164
-4.500 -0.1163 0.00959 0.00322 -0.0483 0.9493 0.0179
-4.250 -0.0869 0.00929 0.00289 -0.0484 0.9333 0.0199
-4.000 -0.0590 0.00908 0.00262 -0.0482 0.9092 0.0223
-3.750 -0.0332 0.00885 0.00228 -0.0473 0.8652 0.0263
-3.500 -0.0075 0.00878 0.00202 -0.0464 0.8308 0.0306
-3.250 0.0191 0.00868 0.00184 -0.0460 0.8028 0.0413
-3.000 0.0460 0.00854 0.00169 -0.0456 0.7774 0.0660
-2.750 0.0730 0.00838 0.00157 -0.0454 0.7524 0.1074
-2.500 0.0999 0.00816 0.00146 -0.0453 0.7258 0.1760
-2.000 0.1529 0.00765 0.00132 -0.0450 0.6387 0.3883
-1.750 0.1786 0.00730 0.00129 -0.0449 0.6031 0.5439
-1.500 0.2030 0.00683 0.00132 -0.0442 0.5811 0.7250
-1.250 0.2223 0.00643 0.00137 -0.0417 0.5646 0.8905
-1.000 0.2608 0.00640 0.00133 -0.0437 0.5480 0.9925
-0.750 0.2905 0.00651 0.00132 -0.0441 0.5341 1.0000
-0.500 0.3180 0.00661 0.00134 -0.0440 0.5213 1.0000
-0.250 0.3456 0.00672 0.00136 -0.0439 0.5087 1.0000
0.000 0.3732 0.00682 0.00139 -0.0438 0.4963 1.0000
0.250 0.4009 0.00692 0.00142 -0.0438 0.4833 1.0000
0.500 0.4286 0.00703 0.00147 -0.0438 0.4694 1.0000
0.750 0.4564 0.00714 0.00152 -0.0437 0.4536 1.0000
1.000 0.4839 0.00728 0.00158 -0.0437 0.4359 1.0000
1.250 0.5115 0.00743 0.00164 -0.0437 0.4156 1.0000
1.500 0.5389 0.00761 0.00173 -0.0436 0.3942 1.0000
1.750 0.5662 0.00779 0.00184 -0.0436 0.3728 1.0000
2.250 0.6206 0.00824 0.00209 -0.0435 0.3277 1.0000
2.500 0.6476 0.00848 0.00224 -0.0435 0.3055 1.0000
2.750 0.6746 0.00873 0.00242 -0.0435 0.2821 1.0000
3.000 0.7015 0.00900 0.00260 -0.0435 0.2587 1.0000
3.250 0.7282 0.00930 0.00279 -0.0434 0.2346 1.0000
3.500 0.7549 0.00960 0.00302 -0.0434 0.2108 1.0000
3.750 0.7814 0.00995 0.00326 -0.0434 0.1856 1.0000
4.000 0.8076 0.01032 0.00353 -0.0433 0.1605 1.0000
4.250 0.8336 0.01073 0.00383 -0.0432 0.1346 1.0000
4.500 0.8594 0.01116 0.00417 -0.0431 0.1124 1.0000
4.750 0.8851 0.01159 0.00452 -0.0430 0.0914 1.0000
5.000 0.9106 0.01206 0.00491 -0.0428 0.0734 1.0000
5.250 0.9362 0.01249 0.00530 -0.0427 0.0607 1.0000
5.500 0.9616 0.01294 0.00572 -0.0425 0.0500 1.0000
5.750 0.9870 0.01336 0.00614 -0.0424 0.0426 1.0000
6.000 1.0124 0.01378 0.00659 -0.0422 0.0373 1.0000
6.250 1.0374 0.01424 0.00705 -0.0420 0.0325 1.0000
6.500 1.0622 0.01472 0.00758 -0.0418 0.0288 1.0000
6.750 1.0871 0.01517 0.00808 -0.0415 0.0262 1.0000
7.000 1.1111 0.01572 0.00866 -0.0412 0.0235 1.0000
7.250 1.1350 0.01628 0.00928 -0.0408 0.0215 1.0000
7.500 1.1591 0.01678 0.00985 -0.0405 0.0198 1.0000
7.750 1.1825 0.01735 0.01049 -0.0402 0.0182 1.0000
8.000 1.2046 0.01808 0.01127 -0.0396 0.0166 1.0000
8.250 1.2270 0.01875 0.01203 -0.0391 0.0156 1.0000
8.500 1.2495 0.01935 0.01272 -0.0387 0.0145 1.0000
8.750 1.2714 0.01999 0.01344 -0.0381 0.0135 1.0000
9.000 1.2922 0.02074 0.01426 -0.0375 0.0126 1.0000
9.250 1.3101 0.02182 0.01544 -0.0365 0.0117 1.0000
9.500 1.3301 0.02257 0.01631 -0.0358 0.0112 1.0000
9.750 1.3494 0.02337 0.01721 -0.0350 0.0105 1.0000
10.000 1.3680 0.02419 0.01814 -0.0341 0.0098 1.0000
10.250 1.3856 0.02506 0.01910 -0.0332 0.0092 1.0000
10.500 1.4007 0.02612 0.02024 -0.0320 0.0087 1.0000
10.750 1.4106 0.02759 0.02184 -0.0302 0.0083 1.0000
11.000 1.4224 0.02877 0.02318 -0.0287 0.0080 1.0000
11.250 1.4302 0.03001 0.02457 -0.0266 0.0077 1.0000
11.500 1.4351 0.03138 0.02607 -0.0242 0.0075 1.0000
11.750 1.4387 0.03293 0.02777 -0.0222 0.0072 1.0000
12.000 1.4417 0.03467 0.02965 -0.0206 0.0069 1.0000
12.250 1.4440 0.03664 0.03175 -0.0195 0.0067 1.0000
12.500 1.4444 0.03903 0.03428 -0.0190 0.0065 1.0000
12.750 1.4440 0.04181 0.03720 -0.0192 0.0063 1.0000
13.000 1.4402 0.04532 0.04086 -0.0200 0.0061 1.0000
13.250 1.4339 0.04956 0.04524 -0.0217 0.0060 1.0000
13.500 1.4237 0.05485 0.05070 -0.0243 0.0059 1.0000
13.750 1.4104 0.06089 0.05690 -0.0274 0.0058 1.0000
14.000 1.3940 0.06751 0.06369 -0.0308 0.0057 1.0000
14.250 1.3748 0.07466 0.07100 -0.0343 0.0057 1.0000
14.500 1.3551 0.08206 0.07854 -0.0378 0.0057 1.0000
14.750 1.3337 0.08984 0.08647 -0.0415 0.0057 1.0000
15.000 1.3120 0.09787 0.09464 -0.0453 0.0057 1.0000
15.250 1.2899 0.10625 0.10315 -0.0492 0.0058 1.0000
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