AG12 (ag12-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG12 (ag12-il) Reynolds number: 100,000 Max Cl/Cd: 46.97 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag12-il-100000-n5.txt Download as CSV file: xf-ag12-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG12
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4633 0.10348 0.09885 0.0037 1.0000 0.0490
-8.750 -0.4670 0.09967 0.09509 0.0008 1.0000 0.0495
-8.500 -0.5614 0.10512 0.10029 0.0149 1.0000 0.0407
-8.250 -0.5556 0.10176 0.09695 0.0137 1.0000 0.0428
-8.000 -0.5516 0.09802 0.09325 0.0116 1.0000 0.0441
-7.500 -0.4627 0.07292 0.06847 -0.0054 1.0000 0.0249
-7.250 -0.5372 0.08012 0.07545 -0.0047 1.0000 0.0251
-7.000 -0.5280 0.07538 0.07072 -0.0083 1.0000 0.0243
-6.750 -0.5156 0.06988 0.06521 -0.0138 1.0000 0.0236
-6.500 -0.4998 0.06361 0.05889 -0.0204 1.0000 0.0229
-6.250 -0.4810 0.05661 0.05176 -0.0274 1.0000 0.0222
-6.000 -0.4598 0.04923 0.04412 -0.0337 1.0000 0.0216
-5.750 -0.4367 0.04232 0.03680 -0.0386 1.0000 0.0210
-5.500 -0.4118 0.03624 0.03016 -0.0420 1.0000 0.0207
-5.250 -0.3856 0.03132 0.02459 -0.0439 1.0000 0.0206
-5.000 -0.3586 0.02749 0.02013 -0.0448 1.0000 0.0209
-4.750 -0.3312 0.02451 0.01658 -0.0451 1.0000 0.0215
-4.500 -0.3039 0.02229 0.01391 -0.0450 1.0000 0.0233
-4.250 -0.2766 0.02065 0.01189 -0.0447 1.0000 0.0264
-4.000 -0.2504 0.01883 0.00995 -0.0445 1.0000 0.0292
-3.750 -0.2237 0.01748 0.00842 -0.0441 1.0000 0.0328
-3.500 -0.1971 0.01635 0.00716 -0.0438 1.0000 0.0400
-3.250 -0.1702 0.01535 0.00611 -0.0435 1.0000 0.0521
-3.000 -0.1435 0.01443 0.00528 -0.0434 1.0000 0.0805
-2.750 -0.1169 0.01355 0.00466 -0.0433 1.0000 0.1380
-2.500 -0.0908 0.01284 0.00427 -0.0433 1.0000 0.2216
-2.250 -0.0649 0.01229 0.00399 -0.0431 1.0000 0.3113
-2.000 -0.0394 0.01184 0.00380 -0.0427 1.0000 0.3987
-1.750 -0.0139 0.01143 0.00364 -0.0421 1.0000 0.4872
-1.500 0.0109 0.01101 0.00351 -0.0414 1.0000 0.5812
-1.250 0.0332 0.01049 0.00337 -0.0398 1.0000 0.7005
-1.000 0.0566 0.00983 0.00317 -0.0380 1.0000 1.0000
-0.750 0.0828 0.00989 0.00307 -0.0378 1.0000 1.0000
-0.500 0.1088 0.00996 0.00303 -0.0377 1.0000 1.0000
-0.250 0.1503 0.01005 0.00297 -0.0407 0.9837 1.0000
0.000 0.1917 0.01011 0.00293 -0.0435 0.9610 1.0000
0.250 0.2316 0.01017 0.00290 -0.0458 0.9347 1.0000
0.500 0.2694 0.01023 0.00287 -0.0475 0.9040 1.0000
0.750 0.3037 0.01030 0.00285 -0.0483 0.8692 1.0000
1.000 0.3341 0.01041 0.00284 -0.0482 0.8315 1.0000
1.250 0.3614 0.01055 0.00285 -0.0474 0.7922 1.0000
1.500 0.3876 0.01074 0.00289 -0.0465 0.7525 1.0000
1.750 0.4134 0.01095 0.00298 -0.0455 0.7128 1.0000
2.000 0.4392 0.01120 0.00307 -0.0446 0.6734 1.0000
2.250 0.4652 0.01146 0.00319 -0.0439 0.6345 1.0000
2.500 0.4911 0.01176 0.00334 -0.0431 0.5964 1.0000
2.750 0.5170 0.01207 0.00352 -0.0425 0.5585 1.0000
3.000 0.5429 0.01240 0.00377 -0.0419 0.5211 1.0000
3.250 0.5688 0.01275 0.00401 -0.0413 0.4846 1.0000
3.500 0.5947 0.01312 0.00428 -0.0408 0.4484 1.0000
3.750 0.6206 0.01351 0.00458 -0.0403 0.4123 1.0000
4.000 0.6464 0.01394 0.00497 -0.0399 0.3768 1.0000
4.250 0.6722 0.01439 0.00535 -0.0395 0.3411 1.0000
4.500 0.6978 0.01487 0.00576 -0.0391 0.3058 1.0000
4.750 0.7233 0.01540 0.00622 -0.0387 0.2708 1.0000
5.000 0.7487 0.01596 0.00674 -0.0383 0.2371 1.0000
5.250 0.7740 0.01659 0.00737 -0.0380 0.2045 1.0000
5.500 0.7989 0.01729 0.00801 -0.0377 0.1739 1.0000
5.750 0.8237 0.01804 0.00874 -0.0373 0.1464 1.0000
6.000 0.8481 0.01888 0.00954 -0.0369 0.1202 1.0000
6.250 0.8724 0.01978 0.01051 -0.0365 0.0987 1.0000
6.500 0.8960 0.02081 0.01152 -0.0361 0.0789 1.0000
6.750 0.9192 0.02199 0.01285 -0.0355 0.0640 1.0000
7.000 0.9420 0.02323 0.01418 -0.0349 0.0506 1.0000
7.250 0.9633 0.02482 0.01587 -0.0341 0.0421 1.0000
7.500 0.9846 0.02627 0.01743 -0.0336 0.0338 1.0000
7.750 1.0050 0.02830 0.01975 -0.0324 0.0296 1.0000
8.000 1.0254 0.02992 0.02155 -0.0318 0.0250 1.0000
8.250 1.0428 0.03237 0.02421 -0.0309 0.0219 1.0000
8.500 1.0605 0.03517 0.02744 -0.0297 0.0203 1.0000
8.750 1.0757 0.03842 0.03114 -0.0286 0.0190 1.0000
9.000 1.0879 0.04184 0.03501 -0.0276 0.0179 1.0000
9.250 1.0982 0.04475 0.03836 -0.0268 0.0166 1.0000
9.500 1.1057 0.04749 0.04132 -0.0262 0.0153 1.0000
10.000 1.0956 0.05649 0.05103 -0.0253 0.0143 1.0000
10.250 1.0826 0.06084 0.05569 -0.0253 0.0142 1.0000
10.500 1.0660 0.06600 0.06109 -0.0276 0.0142 1.0000
10.750 1.0488 0.07258 0.06786 -0.0325 0.0143 1.0000
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Polar data table (+)
Polar graphs
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