AG45c -03f (ag45c03-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG45c -03f (ag45c03-il) Reynolds number: 100,000 Max Cl/Cd: 47.95 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag45c03-il-100000-n5.txt Download as CSV file: xf-ag45c03-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG45c -03f
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5596 0.10543 0.10075 0.0206 1.0000 0.0471
-7.250 -0.5610 0.10189 0.09729 0.0143 1.0000 0.0488
-7.000 -0.5592 0.09788 0.09335 0.0080 1.0000 0.0492
-6.750 -0.5509 0.09285 0.08833 0.0003 1.0000 0.0494
-6.500 -0.4545 0.07505 0.07075 0.0009 1.0000 0.0355
-6.250 -0.4535 0.07057 0.06631 0.0002 1.0000 0.0325
-6.000 -0.4560 0.06451 0.06030 -0.0047 1.0000 0.0298
-5.750 -0.5067 0.06778 0.06314 -0.0125 1.0000 0.0260
-5.500 -0.4946 0.06325 0.05857 -0.0149 1.0000 0.0251
-5.250 -0.4785 0.05797 0.05318 -0.0187 1.0000 0.0243
-5.000 -0.4596 0.05229 0.04732 -0.0225 1.0000 0.0234
-4.750 -0.4385 0.04642 0.04112 -0.0259 1.0000 0.0225
-4.500 -0.4157 0.04068 0.03498 -0.0285 1.0000 0.0218
-4.250 -0.3913 0.03546 0.02925 -0.0303 1.0000 0.0212
-4.000 -0.3657 0.03107 0.02428 -0.0312 1.0000 0.0209
-3.750 -0.3393 0.02761 0.02025 -0.0315 1.0000 0.0210
-3.500 -0.3123 0.02487 0.01702 -0.0315 1.0000 0.0215
-3.250 -0.2852 0.02297 0.01474 -0.0314 1.0000 0.0236
-3.000 -0.2575 0.02134 0.01271 -0.0310 1.0000 0.0260
-2.750 -0.2305 0.01940 0.01051 -0.0306 1.0000 0.0274
-2.500 -0.2041 0.01791 0.00896 -0.0303 1.0000 0.0297
-2.250 -0.1773 0.01686 0.00784 -0.0300 1.0000 0.0342
-2.000 -0.1508 0.01583 0.00677 -0.0297 1.0000 0.0413
-1.750 -0.1240 0.01492 0.00585 -0.0294 1.0000 0.0528
-1.500 -0.0973 0.01404 0.00510 -0.0292 1.0000 0.0819
-1.250 -0.0712 0.01315 0.00462 -0.0292 1.0000 0.1605
-1.000 -0.0365 0.01222 0.00431 -0.0312 0.9654 0.3113
-0.750 -0.0024 0.01098 0.00414 -0.0325 0.9114 0.6004
-0.500 0.0305 0.01017 0.00395 -0.0312 0.8625 0.9190
-0.250 0.0702 0.01020 0.00359 -0.0330 0.8193 1.0000
0.000 0.0972 0.01036 0.00340 -0.0324 0.7884 1.0000
0.250 0.1237 0.01054 0.00327 -0.0317 0.7644 1.0000
0.500 0.1503 0.01073 0.00317 -0.0312 0.7445 1.0000
0.750 0.1772 0.01092 0.00312 -0.0307 0.7270 1.0000
1.000 0.2041 0.01112 0.00312 -0.0303 0.7108 1.0000
1.250 0.2309 0.01132 0.00315 -0.0299 0.6947 1.0000
1.500 0.2579 0.01148 0.00319 -0.0296 0.6780 1.0000
1.750 0.2852 0.01162 0.00323 -0.0293 0.6606 1.0000
2.000 0.3124 0.01175 0.00327 -0.0290 0.6433 1.0000
2.250 0.3394 0.01189 0.00332 -0.0287 0.6260 1.0000
2.500 0.3663 0.01203 0.00336 -0.0283 0.6088 1.0000
2.750 0.3933 0.01217 0.00342 -0.0280 0.5908 1.0000
3.000 0.4202 0.01232 0.00350 -0.0276 0.5721 1.0000
3.250 0.4470 0.01249 0.00362 -0.0273 0.5535 1.0000
3.500 0.4739 0.01267 0.00373 -0.0269 0.5342 1.0000
3.750 0.5007 0.01287 0.00387 -0.0266 0.5141 1.0000
4.000 0.5273 0.01309 0.00402 -0.0262 0.4943 1.0000
4.250 0.5541 0.01331 0.00421 -0.0259 0.4731 1.0000
4.500 0.5807 0.01357 0.00445 -0.0256 0.4522 1.0000
4.750 0.6073 0.01383 0.00470 -0.0253 0.4299 1.0000
5.000 0.6338 0.01412 0.00496 -0.0250 0.4075 1.0000
5.250 0.6602 0.01443 0.00524 -0.0247 0.3843 1.0000
5.500 0.6865 0.01476 0.00561 -0.0244 0.3601 1.0000
5.750 0.7127 0.01513 0.00596 -0.0242 0.3357 1.0000
6.000 0.7386 0.01554 0.00635 -0.0239 0.3113 1.0000
6.250 0.7645 0.01599 0.00679 -0.0237 0.2860 1.0000
6.500 0.7902 0.01648 0.00732 -0.0234 0.2610 1.0000
6.750 0.8157 0.01702 0.00787 -0.0232 0.2363 1.0000
7.000 0.8408 0.01762 0.00846 -0.0230 0.2129 1.0000
7.250 0.8657 0.01827 0.00913 -0.0227 0.1901 1.0000
7.500 0.8905 0.01897 0.00989 -0.0225 0.1684 1.0000
7.750 0.9146 0.01975 0.01069 -0.0223 0.1485 1.0000
8.000 0.9388 0.02057 0.01156 -0.0220 0.1291 1.0000
8.250 0.9623 0.02147 0.01252 -0.0217 0.1116 1.0000
8.500 0.9851 0.02249 0.01356 -0.0215 0.0952 1.0000
8.750 1.0073 0.02361 0.01478 -0.0211 0.0810 1.0000
9.000 1.0290 0.02482 0.01608 -0.0207 0.0679 1.0000
9.250 1.0494 0.02621 0.01756 -0.0203 0.0576 1.0000
9.500 1.0700 0.02755 0.01909 -0.0198 0.0485 1.0000
9.750 1.0880 0.02934 0.02102 -0.0190 0.0427 1.0000
10.000 1.1062 0.03092 0.02276 -0.0185 0.0369 1.0000
10.250 1.1217 0.03301 0.02504 -0.0178 0.0331 1.0000
10.500 1.1371 0.03518 0.02748 -0.0169 0.0302 1.0000
10.750 1.1510 0.03718 0.02970 -0.0163 0.0274 1.0000
11.000 1.1604 0.03983 0.03249 -0.0156 0.0251 1.0000
11.250 1.1699 0.04256 0.03562 -0.0147 0.0235 1.0000
11.500 1.1749 0.04574 0.03916 -0.0139 0.0224 1.0000
11.750 1.1753 0.04916 0.04291 -0.0134 0.0216 1.0000
12.000 1.1692 0.05272 0.04675 -0.0129 0.0211 1.0000
12.250 1.1598 0.05689 0.05119 -0.0141 0.0207 1.0000
12.500 1.1482 0.06193 0.05648 -0.0169 0.0205 1.0000
12.750 1.1337 0.06789 0.06268 -0.0207 0.0204 1.0000
13.000 1.1158 0.07496 0.06998 -0.0255 0.0205 1.0000
13.250 1.0938 0.08342 0.07865 -0.0314 0.0209 1.0000
13.500 1.0680 0.09332 0.08872 -0.0382 0.0214 1.0000
13.750 1.0384 0.10486 0.10038 -0.0458 0.0221 1.0000
14.000 1.0059 0.11802 0.11360 -0.0536 0.0230 1.0000
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Polar data table (+)
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