AG12 (ag12-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG12 (ag12-il) Reynolds number: 200,000 Max Cl/Cd: 61.37 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag12-il-200000.txt Download as CSV file: xf-ag12-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5626 0.10455 0.10111 0.0174 1.0000 0.0345
-8.250 -0.5594 0.10074 0.09734 0.0139 1.0000 0.0358
-8.000 -0.5565 0.09699 0.09364 0.0084 1.0000 0.0367
-7.750 -0.5516 0.09291 0.08961 0.0027 1.0000 0.0371
-7.500 -0.5401 0.08797 0.08467 -0.0042 1.0000 0.0373
-7.250 -0.5259 0.08223 0.07892 -0.0120 1.0000 0.0374
-7.000 -0.5278 0.07581 0.07257 -0.0116 1.0000 0.0386
-6.750 -0.5179 0.07285 0.06961 -0.0109 1.0000 0.0399
-6.500 -0.5038 0.06899 0.06575 -0.0138 1.0000 0.0416
-6.250 -0.4858 0.06403 0.06074 -0.0193 1.0000 0.0439
-6.000 -0.4481 0.05540 0.05159 -0.0352 1.0000 0.0497
-5.750 -0.4347 0.04799 0.04411 -0.0385 1.0000 0.0513
-5.500 -0.4170 0.04528 0.04146 -0.0385 1.0000 0.0535
-5.250 -0.3895 0.04015 0.03578 -0.0432 1.0000 0.0642
-5.000 -0.3701 0.03822 0.03403 -0.0426 1.0000 0.0694
-4.750 -0.3321 0.02652 0.02081 -0.0461 1.0000 0.0393
-4.500 -0.3043 0.02257 0.01647 -0.0461 1.0000 0.0324
-4.250 -0.2751 0.01894 0.01215 -0.0458 1.0000 0.0295
-4.000 -0.2472 0.01681 0.00967 -0.0453 1.0000 0.0295
-3.750 -0.2199 0.01524 0.00789 -0.0449 1.0000 0.0312
-3.500 -0.1927 0.01417 0.00669 -0.0444 1.0000 0.0357
-3.250 -0.1659 0.01283 0.00533 -0.0440 1.0000 0.0433
-3.000 -0.1386 0.01176 0.00426 -0.0437 1.0000 0.0589
-2.750 -0.1111 0.01063 0.00340 -0.0437 1.0000 0.1200
-2.500 -0.0844 0.00976 0.00303 -0.0439 1.0000 0.2362
-2.250 -0.0581 0.00921 0.00287 -0.0438 1.0000 0.3479
-2.000 -0.0322 0.00877 0.00276 -0.0435 1.0000 0.4468
-1.750 -0.0066 0.00834 0.00267 -0.0430 1.0000 0.5456
-1.500 0.0175 0.00783 0.00260 -0.0421 1.0000 0.6647
-1.250 0.0385 0.00698 0.00245 -0.0395 1.0000 1.0000
-1.000 0.0655 0.00702 0.00235 -0.0394 1.0000 1.0000
-0.750 0.0922 0.00708 0.00230 -0.0393 1.0000 1.0000
-0.500 0.1188 0.00716 0.00230 -0.0393 1.0000 1.0000
-0.250 0.1454 0.00727 0.00233 -0.0393 1.0000 1.0000
0.000 0.1878 0.00734 0.00234 -0.0426 0.9891 1.0000
0.250 0.2358 0.00735 0.00231 -0.0467 0.9713 1.0000
0.500 0.2785 0.00734 0.00226 -0.0495 0.9471 1.0000
0.750 0.3159 0.00732 0.00220 -0.0509 0.9165 1.0000
1.000 0.3457 0.00736 0.00215 -0.0506 0.8788 1.0000
1.250 0.3712 0.00747 0.00213 -0.0493 0.8379 1.0000
1.500 0.3956 0.00764 0.00214 -0.0479 0.7961 1.0000
1.750 0.4203 0.00786 0.00220 -0.0467 0.7542 1.0000
2.000 0.4454 0.00810 0.00225 -0.0457 0.7122 1.0000
2.250 0.4708 0.00836 0.00234 -0.0448 0.6706 1.0000
2.500 0.4965 0.00865 0.00244 -0.0440 0.6295 1.0000
2.750 0.5223 0.00894 0.00258 -0.0434 0.5891 1.0000
3.000 0.5483 0.00925 0.00277 -0.0428 0.5492 1.0000
3.250 0.5744 0.00958 0.00295 -0.0423 0.5098 1.0000
3.500 0.6005 0.00992 0.00315 -0.0419 0.4710 1.0000
3.750 0.6266 0.01028 0.00338 -0.0415 0.4323 1.0000
4.000 0.6527 0.01066 0.00367 -0.0411 0.3933 1.0000
4.250 0.6788 0.01106 0.00396 -0.0408 0.3546 1.0000
4.500 0.7049 0.01149 0.00429 -0.0405 0.3162 1.0000
4.750 0.7307 0.01196 0.00465 -0.0402 0.2775 1.0000
5.000 0.7564 0.01250 0.00506 -0.0399 0.2404 1.0000
5.250 0.7820 0.01307 0.00556 -0.0396 0.2030 1.0000
5.500 0.8074 0.01372 0.00612 -0.0393 0.1689 1.0000
5.750 0.8324 0.01445 0.00674 -0.0390 0.1369 1.0000
6.000 0.8571 0.01530 0.00749 -0.0386 0.1095 1.0000
6.250 0.8818 0.01617 0.00834 -0.0382 0.0858 1.0000
6.500 0.9051 0.01740 0.00951 -0.0376 0.0674 1.0000
6.750 0.9291 0.01847 0.01070 -0.0370 0.0520 1.0000
7.000 0.9516 0.02002 0.01231 -0.0362 0.0414 1.0000
7.250 0.9725 0.02198 0.01430 -0.0353 0.0328 1.0000
7.500 0.9960 0.02357 0.01614 -0.0343 0.0286 1.0000
7.750 1.0174 0.02522 0.01788 -0.0336 0.0243 1.0000
8.000 1.0365 0.02828 0.02130 -0.0324 0.0218 1.0000
8.250 1.0561 0.03105 0.02448 -0.0313 0.0206 1.0000
8.500 1.0725 0.03454 0.02847 -0.0300 0.0198 1.0000
8.750 1.0842 0.03881 0.03329 -0.0286 0.0196 1.0000
9.000 1.0896 0.04385 0.03890 -0.0273 0.0198 1.0000
9.250 1.0884 0.04937 0.04494 -0.0263 0.0202 1.0000
9.500 1.0807 0.05499 0.05098 -0.0258 0.0207 1.0000
9.750 1.0670 0.06044 0.05676 -0.0260 0.0210 1.0000
10.000 1.0480 0.06531 0.06183 -0.0267 0.0212 1.0000
10.250 1.0282 0.07144 0.06815 -0.0313 0.0214 1.0000
10.500 1.0086 0.07990 0.07675 -0.0394 0.0215 1.0000
10.750 0.9881 0.09062 0.08756 -0.0488 0.0218 1.0000
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Polar data table (+)
Polar graphs
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