AG04 (ag04-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG04 (ag04-il) Reynolds number: 100,000 Max Cl/Cd: 45.42 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag04-il-100000.txt Download as CSV file: xf-ag04-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG04
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5721 0.11485 0.11004 0.0197 1.0000 0.0753
-8.750 -0.5753 0.11205 0.10731 0.0150 1.0000 0.0779
-8.500 -0.5830 0.10963 0.10498 0.0079 1.0000 0.0787
-8.250 -0.5769 0.10407 0.09947 0.0078 1.0000 0.0799
-8.000 -0.5595 0.09965 0.09501 0.0121 1.0000 0.0831
-7.750 -0.5541 0.09612 0.09152 0.0108 1.0000 0.0865
-7.500 -0.5540 0.09258 0.08805 0.0058 1.0000 0.0903
-7.250 -0.5503 0.08696 0.08242 -0.0118 1.0000 0.0928
-7.000 -0.5398 0.08331 0.07881 -0.0023 1.0000 0.0953
-6.750 -0.5283 0.07963 0.07514 -0.0033 1.0000 0.0994
-6.500 -0.5143 0.07305 0.06842 -0.0190 1.0000 0.1067
-6.250 -0.5028 0.06978 0.06525 -0.0143 1.0000 0.1095
-6.000 -0.4834 0.06421 0.05943 -0.0248 1.0000 0.1204
-5.750 -0.4697 0.06072 0.05606 -0.0219 1.0000 0.1233
-5.500 -0.4492 0.05594 0.05108 -0.0272 1.0000 0.1351
-5.250 -0.4312 0.05268 0.04783 -0.0267 1.0000 0.1418
-5.000 -0.3885 0.03652 0.03026 -0.0374 1.0000 0.0618
-4.750 -0.3632 0.03187 0.02505 -0.0381 1.0000 0.0598
-4.500 -0.3367 0.02800 0.02058 -0.0383 1.0000 0.0596
-4.250 -0.3090 0.02445 0.01637 -0.0379 1.0000 0.0585
-4.000 -0.2813 0.02186 0.01328 -0.0373 1.0000 0.0608
-3.750 -0.2543 0.01985 0.01095 -0.0367 1.0000 0.0691
-3.500 -0.2273 0.01811 0.00898 -0.0359 1.0000 0.0806
-3.250 -0.2011 0.01681 0.00769 -0.0353 1.0000 0.1049
-3.000 -0.1756 0.01547 0.00654 -0.0348 1.0000 0.1447
-2.750 -0.1504 0.01435 0.00568 -0.0342 1.0000 0.2024
-2.500 -0.1258 0.01328 0.00506 -0.0337 1.0000 0.2823
-2.250 -0.1021 0.01214 0.00460 -0.0330 1.0000 0.4211
-2.000 -0.0830 0.01080 0.00434 -0.0305 1.0000 0.6698
-1.750 -0.0448 0.01001 0.00392 -0.0311 1.0000 1.0000
-1.500 -0.0197 0.01002 0.00366 -0.0307 1.0000 1.0000
-1.250 0.0051 0.01005 0.00347 -0.0302 1.0000 1.0000
-1.000 0.0297 0.01010 0.00332 -0.0297 1.0000 1.0000
-0.750 0.0542 0.01016 0.00325 -0.0293 1.0000 1.0000
-0.500 0.0784 0.01026 0.00323 -0.0289 1.0000 1.0000
-0.250 0.1023 0.01038 0.00326 -0.0285 1.0000 1.0000
0.000 0.1262 0.01055 0.00334 -0.0282 1.0000 1.0000
0.250 0.1498 0.01076 0.00351 -0.0280 1.0000 1.0000
0.500 0.1729 0.01104 0.00375 -0.0279 1.0000 1.0000
0.750 0.1977 0.01139 0.00409 -0.0284 0.9988 1.0000
1.000 0.2600 0.01157 0.00428 -0.0358 0.9771 1.0000
1.250 0.3215 0.01160 0.00436 -0.0424 0.9556 1.0000
1.500 0.3707 0.01155 0.00437 -0.0460 0.9277 1.0000
1.750 0.4075 0.01152 0.00439 -0.0468 0.8936 1.0000
2.000 0.4368 0.01152 0.00438 -0.0458 0.8579 1.0000
2.250 0.4610 0.01160 0.00440 -0.0439 0.8184 1.0000
2.500 0.4839 0.01174 0.00446 -0.0417 0.7775 1.0000
2.750 0.5068 0.01195 0.00458 -0.0397 0.7353 1.0000
3.000 0.5299 0.01221 0.00470 -0.0378 0.6920 1.0000
3.250 0.5535 0.01253 0.00487 -0.0362 0.6466 1.0000
3.500 0.5774 0.01290 0.00509 -0.0349 0.6000 1.0000
3.750 0.6014 0.01332 0.00537 -0.0336 0.5539 1.0000
4.000 0.6256 0.01379 0.00567 -0.0325 0.5075 1.0000
4.250 0.6499 0.01431 0.00604 -0.0316 0.4619 1.0000
4.500 0.6742 0.01489 0.00646 -0.0307 0.4182 1.0000
4.750 0.6986 0.01551 0.00693 -0.0299 0.3762 1.0000
5.000 0.7230 0.01618 0.00753 -0.0292 0.3362 1.0000
5.250 0.7472 0.01690 0.00814 -0.0286 0.2978 1.0000
5.500 0.7711 0.01770 0.00878 -0.0279 0.2613 1.0000
5.750 0.7950 0.01854 0.00958 -0.0273 0.2242 1.0000
6.000 0.8185 0.01955 0.01050 -0.0266 0.1895 1.0000
6.250 0.8416 0.02063 0.01156 -0.0259 0.1565 1.0000
6.500 0.8647 0.02201 0.01288 -0.0252 0.1293 1.0000
6.750 0.8875 0.02344 0.01434 -0.0244 0.1060 1.0000
7.000 0.9106 0.02524 0.01614 -0.0235 0.0898 1.0000
7.250 0.9330 0.02705 0.01801 -0.0228 0.0760 1.0000
7.500 0.9559 0.02966 0.02095 -0.0217 0.0671 1.0000
7.750 0.9766 0.03223 0.02371 -0.0209 0.0589 1.0000
8.000 0.9968 0.03548 0.02755 -0.0196 0.0546 1.0000
8.250 1.0143 0.03891 0.03107 -0.0190 0.0499 1.0000
8.500 1.0259 0.04274 0.03570 -0.0175 0.0470 1.0000
8.750 1.0332 0.04771 0.04133 -0.0163 0.0462 1.0000
9.000 1.0345 0.05322 0.04742 -0.0154 0.0463 1.0000
9.250 1.0303 0.05894 0.05359 -0.0150 0.0468 1.0000
9.500 1.0218 0.06463 0.05961 -0.0151 0.0475 1.0000
9.750 1.0099 0.07020 0.06540 -0.0156 0.0481 1.0000
10.000 0.9961 0.07555 0.07087 -0.0163 0.0488 1.0000
10.250 0.9302 0.09280 0.08843 -0.0350 0.0547 1.0000
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Polar data table (+)
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