AG18 (ag18-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG18 (ag18-il) Reynolds number: 100,000 Max Cl/Cd: 48.53 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag18-il-100000-n5.txt Download as CSV file: xf-ag18-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG18
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5526 0.11917 0.11420 0.0153 1.0000 0.0376
-9.000 -0.5498 0.11588 0.11095 0.0120 1.0000 0.0379
-8.750 -0.5461 0.11238 0.10749 0.0090 1.0000 0.0381
-7.750 -0.5215 0.09637 0.09162 0.0072 1.0000 0.0427
-7.500 -0.5161 0.09292 0.08821 0.0053 1.0000 0.0445
-7.250 -0.5104 0.08920 0.08454 0.0024 1.0000 0.0457
-7.000 -0.5014 0.08497 0.08035 -0.0017 1.0000 0.0463
-6.750 -0.4903 0.08037 0.07578 -0.0064 1.0000 0.0457
-6.250 -0.4536 0.06525 0.06053 -0.0235 1.0000 0.0250
-6.000 -0.4352 0.05978 0.05499 -0.0286 1.0000 0.0240
-5.750 -0.4132 0.05370 0.04878 -0.0343 1.0000 0.0231
-5.500 -0.3885 0.04731 0.04214 -0.0397 1.0000 0.0222
-5.250 -0.3619 0.04100 0.03547 -0.0442 1.0000 0.0215
-5.000 -0.3343 0.03533 0.02929 -0.0474 1.0000 0.0209
-4.750 -0.3061 0.03055 0.02390 -0.0494 1.0000 0.0207
-4.500 -0.2778 0.02678 0.01951 -0.0504 1.0000 0.0208
-4.250 -0.2497 0.02384 0.01601 -0.0507 1.0000 0.0213
-4.000 -0.2221 0.02173 0.01341 -0.0506 1.0000 0.0233
-3.750 -0.1946 0.02035 0.01160 -0.0503 1.0000 0.0264
-3.500 -0.1681 0.01822 0.00931 -0.0500 1.0000 0.0287
-3.250 -0.1416 0.01693 0.00791 -0.0496 1.0000 0.0320
-3.000 -0.1151 0.01597 0.00680 -0.0492 1.0000 0.0389
-2.750 -0.0886 0.01499 0.00577 -0.0489 1.0000 0.0505
-2.500 -0.0620 0.01410 0.00493 -0.0487 1.0000 0.0781
-2.250 -0.0355 0.01320 0.00435 -0.0487 1.0000 0.1425
-2.000 -0.0096 0.01245 0.00404 -0.0487 1.0000 0.2529
-1.750 0.0158 0.01187 0.00387 -0.0484 1.0000 0.3798
-1.500 0.0415 0.01136 0.00375 -0.0480 1.0000 0.5055
-1.250 0.0647 0.01075 0.00360 -0.0468 1.0000 0.6539
-1.000 0.0846 0.00998 0.00341 -0.0443 1.0000 1.0000
-0.750 0.1106 0.01007 0.00331 -0.0442 1.0000 1.0000
-0.500 0.1434 0.01017 0.00325 -0.0454 0.9945 1.0000
-0.250 0.1866 0.01025 0.00315 -0.0487 0.9783 1.0000
0.000 0.2275 0.01031 0.00309 -0.0513 0.9594 1.0000
0.250 0.2668 0.01036 0.00305 -0.0535 0.9386 1.0000
0.500 0.3038 0.01041 0.00301 -0.0550 0.9150 1.0000
0.750 0.3376 0.01046 0.00299 -0.0558 0.8882 1.0000
1.000 0.3686 0.01053 0.00297 -0.0559 0.8588 1.0000
1.250 0.3968 0.01063 0.00298 -0.0553 0.8265 1.0000
1.500 0.4238 0.01075 0.00300 -0.0545 0.7927 1.0000
1.750 0.4498 0.01091 0.00308 -0.0535 0.7570 1.0000
2.000 0.4756 0.01111 0.00314 -0.0525 0.7196 1.0000
2.250 0.5014 0.01133 0.00323 -0.0516 0.6799 1.0000
2.500 0.5269 0.01159 0.00335 -0.0507 0.6376 1.0000
2.750 0.5523 0.01189 0.00350 -0.0498 0.5932 1.0000
3.000 0.5776 0.01224 0.00373 -0.0490 0.5474 1.0000
3.250 0.6029 0.01263 0.00395 -0.0483 0.5015 1.0000
3.500 0.6282 0.01305 0.00421 -0.0476 0.4561 1.0000
3.750 0.6535 0.01351 0.00452 -0.0471 0.4127 1.0000
4.000 0.6788 0.01400 0.00487 -0.0465 0.3716 1.0000
4.250 0.7041 0.01451 0.00533 -0.0461 0.3331 1.0000
4.500 0.7293 0.01505 0.00577 -0.0457 0.2975 1.0000
4.750 0.7546 0.01560 0.00626 -0.0453 0.2631 1.0000
5.000 0.7797 0.01619 0.00680 -0.0449 0.2315 1.0000
5.250 0.8048 0.01683 0.00739 -0.0445 0.2019 1.0000
5.500 0.8296 0.01750 0.00809 -0.0441 0.1737 1.0000
5.750 0.8542 0.01825 0.00881 -0.0437 0.1492 1.0000
6.000 0.8787 0.01902 0.00962 -0.0433 0.1253 1.0000
6.250 0.9027 0.01991 0.01053 -0.0428 0.1063 1.0000
6.500 0.9265 0.02084 0.01151 -0.0423 0.0874 1.0000
6.750 0.9496 0.02194 0.01266 -0.0418 0.0729 1.0000
7.000 0.9721 0.02313 0.01397 -0.0412 0.0592 1.0000
7.250 0.9944 0.02444 0.01544 -0.0405 0.0486 1.0000
7.500 1.0159 0.02590 0.01707 -0.0397 0.0394 1.0000
7.750 1.0357 0.02774 0.01905 -0.0388 0.0333 1.0000
8.000 1.0560 0.02956 0.02114 -0.0378 0.0282 1.0000
8.250 1.0735 0.03166 0.02338 -0.0370 0.0238 1.0000
8.500 1.0915 0.03428 0.02643 -0.0358 0.0216 1.0000
8.750 1.1071 0.03731 0.02988 -0.0345 0.0198 1.0000
9.000 1.1211 0.03998 0.03289 -0.0335 0.0180 1.0000
9.250 1.1316 0.04260 0.03571 -0.0327 0.0163 1.0000
9.500 1.1352 0.04673 0.04028 -0.0316 0.0153 1.0000
9.750 1.1364 0.05075 0.04490 -0.0306 0.0146 1.0000
10.000 1.1300 0.05532 0.04991 -0.0298 0.0144 1.0000
10.250 1.1166 0.05985 0.05477 -0.0293 0.0143 1.0000
10.500 1.0994 0.06479 0.05997 -0.0305 0.0144 1.0000
10.750 1.0813 0.07101 0.06640 -0.0346 0.0145 1.0000
11.000 1.0631 0.07885 0.07433 -0.0411 0.0147 1.0000
11.250 1.0444 0.08819 0.08378 -0.0486 0.0150 1.0000
11.500 1.0258 0.09790 0.09354 -0.0553 0.0154 1.0000
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Polar data table (+)
Polar graphs
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