AG37 (ag37-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG37 (ag37-il) Reynolds number: 200,000 Max Cl/Cd: 65.32 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag37-il-200000.txt Download as CSV file: xf-ag37-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5047 0.09804 0.09452 -0.0036 1.0000 0.0389
-9.500 -0.5048 0.09409 0.09062 -0.0086 1.0000 0.0401
-9.250 -0.5057 0.08991 0.08649 -0.0155 1.0000 0.0407
-9.000 -0.4986 0.08453 0.08110 -0.0241 1.0000 0.0410
-8.750 -0.4900 0.07932 0.07580 -0.0299 1.0000 0.0411
-8.500 -0.4912 0.07296 0.06952 -0.0296 1.0000 0.0421
-8.250 -0.4830 0.07036 0.06694 -0.0277 1.0000 0.0432
-8.000 -0.4727 0.06722 0.06379 -0.0283 1.0000 0.0446
-7.750 -0.4610 0.06337 0.05990 -0.0305 1.0000 0.0465
-7.500 -0.4474 0.05884 0.05527 -0.0337 1.0000 0.0492
-7.250 -0.4292 0.05282 0.04855 -0.0401 1.0000 0.0536
-7.000 -0.4194 0.04864 0.04466 -0.0390 1.0000 0.0558
-6.750 -0.4043 0.04653 0.04255 -0.0383 1.0000 0.0591
-6.500 -0.3842 0.04216 0.03747 -0.0402 1.0000 0.0674
-6.250 -0.3598 0.02560 0.02153 -0.0363 1.0000 0.0694
-6.000 -0.3444 0.02334 0.01921 -0.0355 1.0000 0.0727
-5.750 -0.3290 0.03353 0.02850 -0.0390 1.0000 0.0826
-5.500 -0.3091 0.03138 0.02633 -0.0382 1.0000 0.0867
-5.250 -0.2735 0.02245 0.01581 -0.0362 1.0000 0.0395
-5.000 -0.2492 0.02051 0.01351 -0.0353 1.0000 0.0399
-4.750 -0.2246 0.01940 0.01207 -0.0342 1.0000 0.0414
-4.500 -0.1992 0.01743 0.00985 -0.0335 1.0000 0.0416
-4.250 -0.1733 0.01555 0.00784 -0.0330 1.0000 0.0432
-4.000 -0.1484 0.01470 0.00702 -0.0324 1.0000 0.0472
-3.750 -0.1232 0.01409 0.00636 -0.0317 1.0000 0.0519
-3.500 -0.0970 0.01310 0.00539 -0.0314 1.0000 0.0571
-3.250 -0.0712 0.01259 0.00491 -0.0312 1.0000 0.0682
-3.000 -0.0434 0.01188 0.00436 -0.0314 1.0000 0.0991
-2.750 -0.0113 0.00990 0.00415 -0.0334 1.0000 0.5066
-2.500 0.0247 0.00863 0.00419 -0.0336 0.9953 1.0000
-2.250 0.0730 0.00863 0.00397 -0.0379 0.9862 1.0000
-2.000 0.1202 0.00858 0.00377 -0.0419 0.9760 1.0000
-1.750 0.1678 0.00849 0.00355 -0.0459 0.9656 1.0000
-1.500 0.2107 0.00837 0.00334 -0.0488 0.9515 1.0000
-1.250 0.2482 0.00825 0.00314 -0.0504 0.9321 1.0000
-1.000 0.2812 0.00813 0.00295 -0.0510 0.9065 1.0000
-0.750 0.3113 0.00803 0.00274 -0.0508 0.8742 1.0000
-0.500 0.3395 0.00800 0.00255 -0.0501 0.8409 1.0000
-0.250 0.3650 0.00813 0.00249 -0.0490 0.8038 1.0000
0.000 0.3900 0.00832 0.00249 -0.0480 0.7682 1.0000
0.250 0.4153 0.00852 0.00252 -0.0472 0.7331 1.0000
0.500 0.4410 0.00873 0.00256 -0.0465 0.7004 1.0000
0.750 0.4668 0.00893 0.00262 -0.0459 0.6688 1.0000
1.000 0.4927 0.00915 0.00267 -0.0453 0.6404 1.0000
1.250 0.5188 0.00941 0.00278 -0.0449 0.6156 1.0000
1.500 0.5449 0.00972 0.00294 -0.0445 0.5933 1.0000
1.750 0.5713 0.01001 0.00315 -0.0441 0.5717 1.0000
2.000 0.5976 0.01032 0.00335 -0.0438 0.5516 1.0000
2.250 0.6241 0.01056 0.00356 -0.0435 0.5302 1.0000
2.500 0.6504 0.01083 0.00376 -0.0432 0.5095 1.0000
2.750 0.6768 0.01105 0.00398 -0.0430 0.4871 1.0000
3.000 0.7029 0.01129 0.00416 -0.0426 0.4644 1.0000
3.250 0.7292 0.01148 0.00435 -0.0424 0.4385 1.0000
3.500 0.7551 0.01172 0.00455 -0.0421 0.4117 1.0000
3.750 0.7808 0.01201 0.00480 -0.0418 0.3839 1.0000
4.000 0.8063 0.01235 0.00507 -0.0414 0.3556 1.0000
4.250 0.8315 0.01273 0.00538 -0.0411 0.3270 1.0000
4.500 0.8566 0.01314 0.00575 -0.0408 0.2973 1.0000
4.750 0.8813 0.01360 0.00613 -0.0405 0.2657 1.0000
5.000 0.9059 0.01410 0.00655 -0.0402 0.2304 1.0000
5.250 0.9295 0.01474 0.00706 -0.0398 0.1891 1.0000
5.500 0.9519 0.01564 0.00775 -0.0393 0.1440 1.0000
5.750 0.9730 0.01677 0.00867 -0.0386 0.1081 1.0000
6.000 0.9932 0.01800 0.00975 -0.0378 0.0867 1.0000
6.250 1.0135 0.01923 0.01095 -0.0368 0.0740 1.0000
6.500 1.0359 0.02010 0.01191 -0.0361 0.0651 1.0000
6.750 1.0556 0.02146 0.01333 -0.0351 0.0587 1.0000
7.000 1.0766 0.02257 0.01450 -0.0342 0.0536 1.0000
7.250 1.0949 0.02441 0.01636 -0.0331 0.0492 1.0000
7.500 1.1164 0.02551 0.01765 -0.0322 0.0456 1.0000
7.750 1.1367 0.02692 0.01914 -0.0313 0.0426 1.0000
8.000 1.1543 0.02970 0.02198 -0.0304 0.0396 1.0000
8.250 1.1733 0.03106 0.02366 -0.0293 0.0375 1.0000
8.500 1.1912 0.03296 0.02583 -0.0281 0.0356 1.0000
8.750 1.2075 0.03508 0.02820 -0.0269 0.0339 1.0000
9.000 1.2223 0.03699 0.03029 -0.0257 0.0322 1.0000
9.250 1.2328 0.04026 0.03369 -0.0246 0.0305 1.0000
9.500 1.2339 0.04424 0.03812 -0.0224 0.0295 1.0000
9.750 1.2355 0.04706 0.04135 -0.0201 0.0290 1.0000
10.000 1.2307 0.05044 0.04510 -0.0176 0.0287 1.0000
10.250 1.2186 0.05385 0.04884 -0.0146 0.0285 1.0000
10.500 1.2016 0.05747 0.05273 -0.0122 0.0284 1.0000
10.750 1.1826 0.06169 0.05721 -0.0113 0.0284 1.0000
11.000 1.1619 0.06673 0.06248 -0.0122 0.0285 1.0000
11.250 1.1402 0.07269 0.06865 -0.0148 0.0287 1.0000
11.500 1.1174 0.07973 0.07588 -0.0190 0.0289 1.0000
11.750 1.0933 0.08785 0.08415 -0.0243 0.0292 1.0000
12.000 1.0677 0.09698 0.09340 -0.0301 0.0296 1.0000
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Polar data table (+)
Polar graphs
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