AG14 (ag14-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG14 (ag14-il) Reynolds number: 50,000 Max Cl/Cd: 35.76 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag14-il-50000-n5.txt Download as CSV file: xf-ag14-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG14
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5535 0.11768 0.11081 0.0182 1.0000 0.0871
-8.500 -0.5566 0.11565 0.10888 0.0139 1.0000 0.0897
-8.250 -0.5591 0.11338 0.10671 0.0091 1.0000 0.0903
-8.000 -0.5475 0.10791 0.10128 0.0102 1.0000 0.0915
-7.750 -0.5370 0.10353 0.09691 0.0106 1.0000 0.0933
-7.500 -0.5300 0.09984 0.09326 0.0095 1.0000 0.0949
-7.250 -0.5230 0.09616 0.08963 0.0072 1.0000 0.0963
-7.000 -0.4290 0.07802 0.07182 -0.0042 1.0000 0.0579
-6.750 -0.4272 0.07241 0.06623 -0.0100 1.0000 0.0490
-6.500 -0.4843 0.07964 0.07306 -0.0091 1.0000 0.0474
-6.250 -0.4699 0.07495 0.06837 -0.0131 1.0000 0.0456
-6.000 -0.4528 0.06995 0.06333 -0.0180 1.0000 0.0445
-5.750 -0.4331 0.06480 0.05811 -0.0232 1.0000 0.0441
-5.500 -0.4112 0.05960 0.05278 -0.0282 1.0000 0.0441
-5.250 -0.3871 0.05435 0.04733 -0.0329 1.0000 0.0439
-5.000 -0.3610 0.04910 0.04180 -0.0372 1.0000 0.0434
-4.750 -0.3327 0.04380 0.03609 -0.0410 1.0000 0.0423
-4.500 -0.3034 0.03895 0.03064 -0.0439 1.0000 0.0415
-4.250 -0.2741 0.03482 0.02595 -0.0457 1.0000 0.0414
-4.000 -0.2450 0.03137 0.02194 -0.0467 1.0000 0.0422
-3.750 -0.2161 0.02848 0.01852 -0.0472 1.0000 0.0440
-3.500 -0.1870 0.02624 0.01566 -0.0472 1.0000 0.0496
-3.250 -0.1600 0.02418 0.01338 -0.0470 1.0000 0.0549
-3.000 -0.1326 0.02237 0.01126 -0.0463 1.0000 0.0603
-2.750 -0.1061 0.02099 0.00972 -0.0458 1.0000 0.0734
-2.500 -0.0787 0.01964 0.00813 -0.0452 1.0000 0.0908
-2.250 -0.0510 0.01837 0.00701 -0.0452 1.0000 0.1339
-2.000 -0.0234 0.01691 0.00612 -0.0454 1.0000 0.2455
-1.750 0.0000 0.01542 0.00569 -0.0447 1.0000 0.4783
-1.500 0.0182 0.01370 0.00516 -0.0410 1.0000 1.0000
-1.250 0.0450 0.01370 0.00467 -0.0408 1.0000 1.0000
-1.000 0.0712 0.01373 0.00434 -0.0405 1.0000 1.0000
-0.750 0.0971 0.01377 0.00411 -0.0402 1.0000 1.0000
-0.500 0.1227 0.01383 0.00395 -0.0399 1.0000 1.0000
-0.250 0.1481 0.01391 0.00386 -0.0396 1.0000 1.0000
0.000 0.1733 0.01401 0.00380 -0.0393 1.0000 1.0000
0.250 0.1983 0.01414 0.00383 -0.0390 1.0000 1.0000
0.500 0.2230 0.01430 0.00393 -0.0388 1.0000 1.0000
0.750 0.2474 0.01450 0.00410 -0.0387 1.0000 1.0000
1.000 0.2715 0.01474 0.00434 -0.0386 1.0000 1.0000
1.250 0.3187 0.01501 0.00462 -0.0429 0.9749 1.0000
1.500 0.3688 0.01519 0.00485 -0.0473 0.9425 1.0000
1.750 0.4128 0.01531 0.00504 -0.0501 0.9038 1.0000
2.000 0.4529 0.01543 0.00523 -0.0518 0.8609 1.0000
2.250 0.4867 0.01558 0.00537 -0.0519 0.8135 1.0000
2.500 0.5155 0.01580 0.00551 -0.0509 0.7641 1.0000
2.750 0.5410 0.01610 0.00570 -0.0493 0.7133 1.0000
3.000 0.5653 0.01647 0.00594 -0.0476 0.6632 1.0000
3.250 0.5890 0.01690 0.00630 -0.0460 0.6138 1.0000
3.500 0.6128 0.01739 0.00666 -0.0446 0.5650 1.0000
3.750 0.6365 0.01793 0.00706 -0.0433 0.5182 1.0000
4.000 0.6604 0.01851 0.00753 -0.0422 0.4725 1.0000
4.250 0.6844 0.01914 0.00806 -0.0412 0.4281 1.0000
4.500 0.7084 0.01981 0.00876 -0.0403 0.3853 1.0000
4.750 0.7328 0.02054 0.00944 -0.0396 0.3437 1.0000
5.000 0.7574 0.02134 0.01020 -0.0391 0.3038 1.0000
5.250 0.7818 0.02222 0.01105 -0.0385 0.2669 1.0000
5.500 0.8059 0.02319 0.01201 -0.0380 0.2324 1.0000
5.750 0.8297 0.02426 0.01315 -0.0374 0.2016 1.0000
6.000 0.8533 0.02543 0.01437 -0.0368 0.1737 1.0000
6.250 0.8765 0.02675 0.01576 -0.0362 0.1502 1.0000
6.500 0.8995 0.02814 0.01730 -0.0356 0.1274 1.0000
6.750 0.9217 0.02980 0.01902 -0.0348 0.1105 1.0000
7.000 0.9435 0.03152 0.02094 -0.0341 0.0930 1.0000
7.250 0.9649 0.03367 0.02340 -0.0332 0.0805 1.0000
7.500 0.9851 0.03587 0.02580 -0.0324 0.0689 1.0000
7.750 1.0043 0.03820 0.02841 -0.0317 0.0592 1.0000
8.000 1.0224 0.04196 0.03278 -0.0306 0.0537 1.0000
8.250 1.0380 0.04435 0.03533 -0.0300 0.0470 1.0000
8.500 1.0490 0.04879 0.04047 -0.0293 0.0431 1.0000
8.750 1.0551 0.05389 0.04621 -0.0288 0.0412 1.0000
9.000 1.0556 0.05922 0.05206 -0.0287 0.0401 1.0000
9.250 1.0499 0.06478 0.05805 -0.0291 0.0395 1.0000
9.500 1.0374 0.07068 0.06429 -0.0305 0.0394 1.0000
9.750 1.0174 0.07697 0.07078 -0.0331 0.0399 1.0000
10.000 0.9954 0.08469 0.07861 -0.0391 0.0409 1.0000
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Polar data table (+)
Polar graphs
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