AG14 (ag14-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG14 (ag14-il) Reynolds number: 100,000 Max Cl/Cd: 48.68 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag14-il-100000.txt Download as CSV file: xf-ag14-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4362 0.09653 0.09200 0.0053 1.0000 0.0737
-8.000 -0.4411 0.09368 0.08920 0.0023 1.0000 0.0758
-7.750 -0.4497 0.09124 0.08684 -0.0022 1.0000 0.0766
-7.250 -0.4306 0.08111 0.07676 0.0006 1.0000 0.0812
-7.000 -0.4272 0.07745 0.07314 -0.0002 1.0000 0.0846
-6.750 -0.4277 0.07385 0.06960 -0.0038 1.0000 0.0881
-6.500 -0.4240 0.06901 0.06469 -0.0211 1.0000 0.0904
-6.250 -0.4167 0.06440 0.06022 -0.0105 1.0000 0.0933
-6.000 -0.4067 0.06040 0.05623 -0.0114 1.0000 0.0984
-5.750 -0.3930 0.05406 0.04978 -0.0243 1.0000 0.1048
-5.500 -0.3835 0.05065 0.04641 -0.0196 1.0000 0.1085
-5.250 -0.3644 0.04485 0.04045 -0.0284 1.0000 0.1188
-5.000 -0.3522 0.04160 0.03727 -0.0259 1.0000 0.1241
-4.750 -0.3330 0.03692 0.03249 -0.0299 1.0000 0.1349
-4.500 -0.3298 0.04743 0.04235 -0.0369 1.0000 0.1471
-4.250 -0.3000 0.04496 0.03955 -0.0406 1.0000 0.1719
-4.000 -0.2830 0.04099 0.03578 -0.0391 1.0000 0.1777
-3.750 -0.2148 0.02786 0.02057 -0.0481 1.0000 0.0615
-3.500 -0.1849 0.02501 0.01716 -0.0484 1.0000 0.0624
-3.250 -0.1557 0.02215 0.01384 -0.0483 1.0000 0.0617
-3.000 -0.1265 0.01983 0.01107 -0.0478 1.0000 0.0621
-2.750 -0.0982 0.01772 0.00869 -0.0473 1.0000 0.0654
-2.500 -0.0713 0.01636 0.00726 -0.0468 1.0000 0.0795
-2.250 -0.0442 0.01490 0.00590 -0.0463 1.0000 0.0995
-2.000 -0.0172 0.01340 0.00477 -0.0459 1.0000 0.1677
-1.750 0.0078 0.01123 0.00419 -0.0457 1.0000 0.4973
-1.500 0.0274 0.00970 0.00376 -0.0423 1.0000 1.0000
-1.250 0.0543 0.00972 0.00340 -0.0421 1.0000 1.0000
-1.000 0.0808 0.00974 0.00317 -0.0418 1.0000 1.0000
-0.750 0.1071 0.00979 0.00302 -0.0415 1.0000 1.0000
-0.500 0.1332 0.00985 0.00292 -0.0413 1.0000 1.0000
-0.250 0.1592 0.00993 0.00288 -0.0410 1.0000 1.0000
0.000 0.1850 0.01003 0.00287 -0.0408 1.0000 1.0000
0.250 0.2106 0.01015 0.00293 -0.0407 1.0000 1.0000
0.500 0.2359 0.01031 0.00305 -0.0406 1.0000 1.0000
0.750 0.2613 0.01052 0.00324 -0.0406 1.0000 1.0000
1.000 0.2862 0.01079 0.00352 -0.0408 1.0000 1.0000
1.250 0.3167 0.01112 0.00388 -0.0423 0.9961 1.0000
1.500 0.3824 0.01122 0.00406 -0.0501 0.9689 1.0000
1.750 0.4355 0.01116 0.00409 -0.0546 0.9334 1.0000
2.000 0.4769 0.01109 0.00409 -0.0561 0.8903 1.0000
2.250 0.5068 0.01112 0.00408 -0.0550 0.8401 1.0000
2.500 0.5313 0.01128 0.00411 -0.0529 0.7865 1.0000
2.750 0.5543 0.01156 0.00421 -0.0508 0.7313 1.0000
3.000 0.5774 0.01192 0.00442 -0.0488 0.6760 1.0000
3.250 0.6008 0.01235 0.00463 -0.0472 0.6217 1.0000
3.500 0.6245 0.01283 0.00489 -0.0458 0.5691 1.0000
3.750 0.6486 0.01336 0.00520 -0.0447 0.5180 1.0000
4.000 0.6730 0.01392 0.00558 -0.0437 0.4680 1.0000
4.250 0.6972 0.01454 0.00605 -0.0428 0.4208 1.0000
4.500 0.7217 0.01518 0.00655 -0.0421 0.3731 1.0000
4.750 0.7461 0.01589 0.00710 -0.0413 0.3281 1.0000
5.000 0.7704 0.01669 0.00773 -0.0407 0.2856 1.0000
5.250 0.7947 0.01757 0.00848 -0.0401 0.2457 1.0000
5.500 0.8190 0.01857 0.00945 -0.0394 0.2106 1.0000
5.750 0.8432 0.01962 0.01042 -0.0388 0.1798 1.0000
6.000 0.8674 0.02084 0.01161 -0.0382 0.1537 1.0000
6.250 0.8913 0.02215 0.01293 -0.0375 0.1305 1.0000
6.500 0.9151 0.02366 0.01440 -0.0369 0.1110 1.0000
6.750 0.9385 0.02534 0.01622 -0.0361 0.0925 1.0000
7.000 0.9620 0.02757 0.01865 -0.0352 0.0787 1.0000
7.250 0.9841 0.02959 0.02096 -0.0344 0.0654 1.0000
7.500 1.0051 0.03317 0.02462 -0.0336 0.0580 1.0000
7.750 1.0257 0.03522 0.02731 -0.0323 0.0503 1.0000
8.000 1.0419 0.03964 0.03194 -0.0317 0.0464 1.0000
8.250 1.0541 0.04442 0.03748 -0.0304 0.0454 1.0000
8.500 1.0617 0.04983 0.04356 -0.0293 0.0451 1.0000
8.750 1.0640 0.05556 0.04986 -0.0287 0.0451 1.0000
9.000 1.0611 0.06137 0.05613 -0.0286 0.0452 1.0000
9.250 1.0538 0.06723 0.06233 -0.0290 0.0453 1.0000
9.500 1.0433 0.07309 0.06841 -0.0298 0.0457 1.0000
9.750 1.0336 0.07919 0.07460 -0.0307 0.0462 1.0000
10.000 0.8653 0.08289 0.07884 -0.0336 0.0542 1.0000
10.250 0.8453 0.09166 0.08759 -0.0377 0.0559 1.0000
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Polar data table (+)
Polar graphs
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