AG17 (ag17-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG17 (ag17-il) Reynolds number: 50,000 Max Cl/Cd: 36.33 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag17-il-50000-n5.txt Download as CSV file: xf-ag17-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG17
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5347 0.10167 0.09485 0.0046 1.0000 0.0466
-8.000 -0.5298 0.09764 0.09086 0.0030 1.0000 0.0448
-7.750 -0.5262 0.09347 0.08676 0.0007 1.0000 0.0431
-7.500 -0.5221 0.08900 0.08236 -0.0028 1.0000 0.0417
-7.000 -0.5016 0.07459 0.06793 -0.0218 1.0000 0.0369
-6.750 -0.4892 0.06909 0.06237 -0.0262 1.0000 0.0367
-6.500 -0.4750 0.06332 0.05647 -0.0312 1.0000 0.0368
-6.000 -0.4452 0.05499 0.04802 -0.0362 1.0000 0.0399
-5.750 -0.4248 0.04972 0.04246 -0.0403 1.0000 0.0405
-5.500 -0.4018 0.04438 0.03668 -0.0438 1.0000 0.0407
-5.250 -0.3766 0.03944 0.03118 -0.0465 1.0000 0.0407
-5.000 -0.3504 0.03530 0.02646 -0.0480 1.0000 0.0414
-4.750 -0.3234 0.03182 0.02241 -0.0488 1.0000 0.0428
-4.500 -0.2959 0.02895 0.01896 -0.0491 1.0000 0.0459
-4.250 -0.2692 0.02669 0.01630 -0.0490 1.0000 0.0521
-4.000 -0.2427 0.02475 0.01409 -0.0486 1.0000 0.0581
-3.750 -0.2166 0.02291 0.01197 -0.0479 1.0000 0.0658
-3.500 -0.1906 0.02156 0.01051 -0.0476 1.0000 0.0836
-3.250 -0.1641 0.02015 0.00907 -0.0472 1.0000 0.1111
-3.000 -0.1368 0.01878 0.00790 -0.0473 1.0000 0.1704
-2.750 -0.1104 0.01763 0.00722 -0.0474 1.0000 0.2718
-2.500 -0.0854 0.01682 0.00679 -0.0469 1.0000 0.3848
-2.250 -0.0620 0.01616 0.00640 -0.0459 1.0000 0.4908
-2.000 -0.0407 0.01548 0.00607 -0.0441 1.0000 0.5973
-1.750 -0.0235 0.01469 0.00575 -0.0410 1.0000 0.7303
-1.500 0.0034 0.01403 0.00524 -0.0400 1.0000 1.0000
-1.250 0.0299 0.01407 0.00493 -0.0401 1.0000 1.0000
-1.000 0.0558 0.01413 0.00467 -0.0401 1.0000 1.0000
-0.750 0.0813 0.01421 0.00453 -0.0400 1.0000 1.0000
-0.500 0.1064 0.01433 0.00446 -0.0398 1.0000 1.0000
-0.250 0.1311 0.01447 0.00446 -0.0397 1.0000 1.0000
0.000 0.1555 0.01466 0.00450 -0.0396 1.0000 1.0000
0.250 0.1796 0.01488 0.00464 -0.0395 1.0000 1.0000
0.500 0.2041 0.01515 0.00485 -0.0396 0.9996 1.0000
0.750 0.2531 0.01543 0.00508 -0.0444 0.9775 1.0000
1.000 0.3026 0.01566 0.00529 -0.0488 0.9556 1.0000
1.250 0.3476 0.01581 0.00547 -0.0522 0.9304 1.0000
1.500 0.3890 0.01594 0.00562 -0.0545 0.9029 1.0000
1.750 0.4270 0.01604 0.00580 -0.0558 0.8731 1.0000
2.000 0.4599 0.01616 0.00594 -0.0560 0.8398 1.0000
2.250 0.4903 0.01629 0.00607 -0.0556 0.8055 1.0000
2.500 0.5177 0.01647 0.00623 -0.0545 0.7690 1.0000
2.750 0.5437 0.01668 0.00640 -0.0531 0.7316 1.0000
3.000 0.5686 0.01694 0.00667 -0.0516 0.6930 1.0000
3.250 0.5930 0.01725 0.00692 -0.0501 0.6528 1.0000
3.500 0.6171 0.01761 0.00721 -0.0486 0.6116 1.0000
3.750 0.6410 0.01803 0.00755 -0.0472 0.5694 1.0000
4.000 0.6649 0.01849 0.00802 -0.0460 0.5265 1.0000
4.250 0.6887 0.01902 0.00848 -0.0448 0.4837 1.0000
4.500 0.7124 0.01961 0.00901 -0.0437 0.4414 1.0000
4.750 0.7364 0.02027 0.00961 -0.0428 0.3998 1.0000
5.000 0.7604 0.02100 0.01029 -0.0420 0.3590 1.0000
5.250 0.7843 0.02181 0.01113 -0.0413 0.3198 1.0000
5.500 0.8077 0.02269 0.01197 -0.0406 0.2824 1.0000
5.750 0.8311 0.02365 0.01295 -0.0400 0.2454 1.0000
6.000 0.8540 0.02472 0.01400 -0.0394 0.2116 1.0000
6.250 0.8766 0.02590 0.01523 -0.0387 0.1797 1.0000
6.500 0.8987 0.02725 0.01661 -0.0380 0.1521 1.0000
6.750 0.9201 0.02869 0.01809 -0.0373 0.1261 1.0000
7.000 0.9409 0.03043 0.01992 -0.0364 0.1076 1.0000
7.250 0.9616 0.03218 0.02188 -0.0356 0.0882 1.0000
7.500 0.9821 0.03444 0.02432 -0.0346 0.0763 1.0000
7.750 1.0009 0.03659 0.02667 -0.0337 0.0645 1.0000
8.000 1.0188 0.03900 0.02915 -0.0328 0.0567 1.0000
8.250 1.0368 0.04250 0.03327 -0.0316 0.0512 1.0000
8.500 1.0512 0.04488 0.03575 -0.0309 0.0451 1.0000
8.750 1.0620 0.04899 0.04050 -0.0299 0.0417 1.0000
9.000 1.0680 0.05368 0.04579 -0.0289 0.0399 1.0000
9.250 1.0685 0.05856 0.05118 -0.0283 0.0387 1.0000
9.500 1.0633 0.06353 0.05656 -0.0281 0.0379 1.0000
9.750 1.0520 0.06867 0.06204 -0.0285 0.0375 1.0000
10.000 1.0325 0.07417 0.06779 -0.0297 0.0379 1.0000
10.250 1.0095 0.08102 0.07482 -0.0338 0.0387 1.0000
10.500 0.9870 0.08955 0.08345 -0.0406 0.0397 1.0000
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Polar data table (+)
Polar graphs
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