AG46c -03f (ag46c03-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG46c -03f (ag46c03-il) Reynolds number: 50,000 Max Cl/Cd: 33.28 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag46c03-il-50000-n5.txt Download as CSV file: xf-ag46c03-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG46c -03f
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5934 0.11852 0.11179 0.0269 1.0000 0.0949
-7.750 -0.6004 0.11635 0.10973 0.0215 1.0000 0.0972
-7.500 -0.6048 0.11355 0.10708 0.0160 1.0000 0.0978
-7.250 -0.5877 0.10750 0.10098 0.0195 1.0000 0.0994
-7.000 -0.5794 0.10336 0.09687 0.0190 1.0000 0.1010
-6.750 -0.5737 0.09950 0.09306 0.0174 1.0000 0.1022
-6.250 -0.5548 0.08681 0.08031 0.0031 1.0000 0.0556
-6.000 -0.5448 0.08229 0.07581 0.0019 1.0000 0.0514
-5.750 -0.5280 0.07444 0.06777 -0.0094 1.0000 0.0439
-5.500 -0.5160 0.07018 0.06351 -0.0105 1.0000 0.0427
-5.250 -0.5011 0.06544 0.05869 -0.0133 1.0000 0.0416
-5.000 -0.4839 0.06045 0.05356 -0.0166 1.0000 0.0405
-4.750 -0.4644 0.05541 0.04830 -0.0198 1.0000 0.0399
-4.500 -0.4428 0.05054 0.04313 -0.0227 1.0000 0.0402
-4.250 -0.4193 0.04590 0.03808 -0.0251 1.0000 0.0412
-4.000 -0.3942 0.04155 0.03322 -0.0268 1.0000 0.0421
-3.750 -0.3683 0.03765 0.02879 -0.0278 1.0000 0.0426
-3.500 -0.3415 0.03412 0.02470 -0.0284 1.0000 0.0429
-3.250 -0.3139 0.03098 0.02093 -0.0285 1.0000 0.0436
-3.000 -0.2861 0.02822 0.01768 -0.0283 1.0000 0.0450
-2.750 -0.2603 0.02630 0.01565 -0.0283 1.0000 0.0505
-2.500 -0.2322 0.02442 0.01334 -0.0277 1.0000 0.0561
-2.250 -0.2055 0.02256 0.01136 -0.0270 1.0000 0.0611
-2.000 -0.1787 0.02123 0.00992 -0.0265 1.0000 0.0744
-1.750 -0.1516 0.01991 0.00845 -0.0259 1.0000 0.0915
-1.500 -0.1247 0.01861 0.00727 -0.0256 1.0000 0.1304
-1.250 -0.0988 0.01698 0.00633 -0.0257 1.0000 0.2483
-1.000 -0.0853 0.01457 0.00597 -0.0224 1.0000 0.6585
-0.750 -0.0435 0.01378 0.00526 -0.0234 1.0000 1.0000
-0.500 -0.0177 0.01375 0.00483 -0.0231 1.0000 1.0000
-0.250 0.0079 0.01374 0.00454 -0.0228 1.0000 1.0000
0.000 0.0331 0.01375 0.00432 -0.0225 1.0000 1.0000
0.250 0.0579 0.01378 0.00418 -0.0223 1.0000 1.0000
0.500 0.0822 0.01385 0.00409 -0.0220 1.0000 1.0000
0.750 0.1055 0.01396 0.00411 -0.0217 1.0000 1.0000
1.000 0.1284 0.01414 0.00421 -0.0217 0.9990 1.0000
1.250 0.1761 0.01436 0.00431 -0.0261 0.9647 1.0000
1.500 0.2214 0.01456 0.00441 -0.0298 0.9302 1.0000
1.750 0.2630 0.01474 0.00451 -0.0324 0.8954 1.0000
2.000 0.2997 0.01494 0.00463 -0.0337 0.8611 1.0000
2.250 0.3315 0.01517 0.00476 -0.0338 0.8290 1.0000
2.500 0.3590 0.01544 0.00492 -0.0331 0.7981 1.0000
2.750 0.3847 0.01574 0.00512 -0.0319 0.7690 1.0000
3.000 0.4095 0.01609 0.00536 -0.0306 0.7411 1.0000
3.250 0.4339 0.01647 0.00565 -0.0293 0.7140 1.0000
3.500 0.4585 0.01686 0.00605 -0.0281 0.6848 1.0000
3.750 0.4829 0.01718 0.00638 -0.0270 0.6541 1.0000
4.000 0.5074 0.01745 0.00666 -0.0260 0.6217 1.0000
4.250 0.5317 0.01770 0.00691 -0.0248 0.5878 1.0000
4.500 0.5559 0.01797 0.00721 -0.0236 0.5521 1.0000
4.750 0.5800 0.01827 0.00746 -0.0223 0.5144 1.0000
5.000 0.6041 0.01865 0.00778 -0.0213 0.4738 1.0000
5.250 0.6282 0.01911 0.00816 -0.0203 0.4318 1.0000
5.500 0.6522 0.01966 0.00862 -0.0194 0.3893 1.0000
5.750 0.6766 0.02033 0.00927 -0.0188 0.3474 1.0000
6.000 0.7010 0.02110 0.00997 -0.0183 0.3068 1.0000
6.250 0.7254 0.02197 0.01080 -0.0179 0.2699 1.0000
6.500 0.7493 0.02294 0.01172 -0.0174 0.2378 1.0000
6.750 0.7729 0.02399 0.01280 -0.0170 0.2095 1.0000
7.000 0.7965 0.02513 0.01399 -0.0166 0.1844 1.0000
7.250 0.8197 0.02636 0.01529 -0.0160 0.1629 1.0000
7.500 0.8426 0.02767 0.01668 -0.0155 0.1434 1.0000
7.750 0.8649 0.02910 0.01813 -0.0150 0.1271 1.0000
8.000 0.8874 0.03071 0.01991 -0.0144 0.1123 1.0000
8.250 0.9091 0.03238 0.02184 -0.0139 0.0983 1.0000
8.500 0.9308 0.03437 0.02404 -0.0133 0.0883 1.0000
8.750 0.9510 0.03639 0.02640 -0.0128 0.0772 1.0000
9.000 0.9705 0.03919 0.02957 -0.0121 0.0704 1.0000
9.250 0.9885 0.04176 0.03242 -0.0116 0.0640 1.0000
9.500 1.0028 0.04504 0.03619 -0.0113 0.0579 1.0000
9.750 1.0149 0.04872 0.04035 -0.0110 0.0540 1.0000
10.000 1.0256 0.05224 0.04415 -0.0107 0.0514 1.0000
10.250 1.0300 0.05667 0.04891 -0.0108 0.0494 1.0000
10.500 1.0228 0.06241 0.05523 -0.0118 0.0483 1.0000
10.750 1.0096 0.06830 0.06150 -0.0137 0.0479 1.0000
11.000 0.9916 0.07417 0.06758 -0.0164 0.0481 1.0000
11.250 0.9730 0.08101 0.07453 -0.0215 0.0487 1.0000
11.500 0.9557 0.08877 0.08233 -0.0274 0.0493 1.0000
11.750 0.9401 0.09707 0.09064 -0.0332 0.0498 1.0000
12.000 0.9266 0.10545 0.09900 -0.0384 0.0501 1.0000
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Polar data table (+)
Polar graphs
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