AG08 (ag08-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG08 (ag08-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.25 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag08-il-1000000-n5.txt Download as CSV file: xf-ag08-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG08
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6273 0.10579 0.10421 0.0240 1.0000 0.0028
-9.250 -0.6285 0.10065 0.09909 0.0216 1.0000 0.0028
-9.000 -0.7748 0.02935 0.02694 -0.0375 1.0000 0.0026
-8.750 -0.7635 0.02099 0.01767 -0.0399 1.0000 0.0028
-8.500 -0.7409 0.01876 0.01512 -0.0401 1.0000 0.0029
-8.250 -0.7161 0.01755 0.01374 -0.0401 1.0000 0.0031
-8.000 -0.6907 0.01662 0.01267 -0.0400 1.0000 0.0032
-7.750 -0.6650 0.01574 0.01163 -0.0400 1.0000 0.0034
-7.500 -0.6392 0.01487 0.01061 -0.0399 1.0000 0.0036
-7.250 -0.6131 0.01402 0.00962 -0.0397 1.0000 0.0038
-7.000 -0.5869 0.01323 0.00867 -0.0396 1.0000 0.0040
-6.750 -0.5605 0.01251 0.00782 -0.0394 1.0000 0.0042
-6.500 -0.5339 0.01187 0.00706 -0.0393 1.0000 0.0044
-6.250 -0.5071 0.01132 0.00641 -0.0391 1.0000 0.0045
-6.000 -0.4804 0.01065 0.00561 -0.0389 1.0000 0.0048
-5.750 -0.4536 0.01009 0.00498 -0.0387 1.0000 0.0054
-5.500 -0.4267 0.00978 0.00464 -0.0385 1.0000 0.0060
-5.250 -0.3997 0.00947 0.00430 -0.0383 1.0000 0.0067
-5.000 -0.3728 0.00915 0.00393 -0.0381 1.0000 0.0072
-4.750 -0.3459 0.00879 0.00351 -0.0378 1.0000 0.0077
-4.500 -0.3192 0.00839 0.00306 -0.0375 1.0000 0.0089
-4.250 -0.2926 0.00813 0.00278 -0.0372 1.0000 0.0101
-4.000 -0.2607 0.00791 0.00254 -0.0381 0.9957 0.0114
-3.750 -0.2276 0.00760 0.00222 -0.0392 0.9878 0.0139
-3.500 -0.1944 0.00737 0.00198 -0.0403 0.9772 0.0167
-3.250 -0.1622 0.00717 0.00176 -0.0411 0.9615 0.0205
-3.000 -0.1332 0.00701 0.00158 -0.0411 0.9396 0.0256
-2.750 -0.1072 0.00689 0.00142 -0.0405 0.9109 0.0337
-2.500 -0.0816 0.00683 0.00128 -0.0397 0.8777 0.0417
-2.250 -0.0556 0.00679 0.00114 -0.0391 0.8430 0.0528
-2.000 -0.0290 0.00678 0.00103 -0.0387 0.8056 0.0641
-1.750 -0.0021 0.00677 0.00093 -0.0384 0.7683 0.0804
-1.500 0.0251 0.00677 0.00085 -0.0381 0.7312 0.0980
-1.250 0.0525 0.00675 0.00078 -0.0380 0.6935 0.1222
-1.000 0.0799 0.00675 0.00072 -0.0378 0.6561 0.1486
-0.750 0.1074 0.00674 0.00068 -0.0378 0.6203 0.1825
-0.500 0.1350 0.00672 0.00065 -0.0377 0.5849 0.2200
-0.250 0.1626 0.00672 0.00064 -0.0377 0.5479 0.2643
0.000 0.1902 0.00673 0.00064 -0.0377 0.5131 0.3058
0.250 0.2178 0.00670 0.00065 -0.0377 0.4804 0.3635
0.500 0.2454 0.00665 0.00068 -0.0377 0.4502 0.4259
0.750 0.2729 0.00655 0.00072 -0.0377 0.4200 0.5137
1.000 0.2996 0.00624 0.00077 -0.0377 0.3925 0.6704
1.250 0.3245 0.00554 0.00081 -0.0367 0.3685 1.0000
1.500 0.3522 0.00571 0.00086 -0.0366 0.3428 1.0000
1.750 0.3799 0.00586 0.00092 -0.0365 0.3190 1.0000
2.000 0.4076 0.00602 0.00099 -0.0364 0.2976 1.0000
2.250 0.4352 0.00620 0.00106 -0.0364 0.2746 1.0000
2.500 0.4629 0.00637 0.00115 -0.0363 0.2533 1.0000
2.750 0.4905 0.00656 0.00126 -0.0362 0.2328 1.0000
3.000 0.5180 0.00675 0.00137 -0.0361 0.2122 1.0000
3.250 0.5455 0.00695 0.00149 -0.0360 0.1919 1.0000
3.500 0.5730 0.00715 0.00162 -0.0360 0.1737 1.0000
3.750 0.6003 0.00738 0.00178 -0.0359 0.1535 1.0000
4.000 0.6276 0.00763 0.00195 -0.0358 0.1341 1.0000
4.250 0.6548 0.00790 0.00213 -0.0357 0.1133 1.0000
4.500 0.6818 0.00819 0.00234 -0.0355 0.0938 1.0000
4.750 0.7087 0.00852 0.00259 -0.0354 0.0732 1.0000
5.000 0.7355 0.00885 0.00284 -0.0353 0.0559 1.0000
5.250 0.7623 0.00917 0.00311 -0.0351 0.0427 1.0000
5.500 0.7890 0.00952 0.00341 -0.0350 0.0310 1.0000
5.750 0.8156 0.00988 0.00372 -0.0348 0.0215 1.0000
6.000 0.8421 0.01023 0.00407 -0.0346 0.0156 1.0000
6.250 0.8686 0.01061 0.00444 -0.0344 0.0115 1.0000
6.500 0.8951 0.01095 0.00480 -0.0342 0.0095 1.0000
6.750 0.9213 0.01135 0.00522 -0.0339 0.0077 1.0000
7.000 0.9474 0.01178 0.00569 -0.0337 0.0065 1.0000
7.250 0.9736 0.01215 0.00612 -0.0334 0.0058 1.0000
7.500 0.9994 0.01258 0.00660 -0.0332 0.0052 1.0000
7.750 1.0249 0.01309 0.00716 -0.0329 0.0047 1.0000
8.000 1.0496 0.01382 0.00798 -0.0324 0.0041 1.0000
8.250 1.0747 0.01436 0.00861 -0.0321 0.0040 1.0000
8.500 1.0996 0.01492 0.00924 -0.0317 0.0038 1.0000
8.750 1.1242 0.01553 0.00996 -0.0313 0.0037 1.0000
9.000 1.1484 0.01619 0.01072 -0.0309 0.0035 1.0000
9.250 1.1722 0.01689 0.01152 -0.0304 0.0033 1.0000
9.500 1.1956 0.01764 0.01236 -0.0299 0.0031 1.0000
9.750 1.2186 0.01842 0.01324 -0.0294 0.0029 1.0000
10.000 1.2412 0.01925 0.01418 -0.0289 0.0028 1.0000
10.250 1.2628 0.02021 0.01525 -0.0283 0.0026 1.0000
10.500 1.2828 0.02142 0.01660 -0.0275 0.0025 1.0000
10.750 1.2969 0.02361 0.01907 -0.0263 0.0022 1.0000
11.000 1.3158 0.02481 0.02043 -0.0255 0.0022 1.0000
11.250 1.3343 0.02596 0.02172 -0.0247 0.0022 1.0000
11.500 1.3509 0.02735 0.02327 -0.0238 0.0021 1.0000
11.750 1.3648 0.02901 0.02512 -0.0227 0.0021 1.0000
12.000 1.3763 0.03084 0.02714 -0.0215 0.0020 1.0000
12.250 1.3842 0.03294 0.02945 -0.0201 0.0020 1.0000
12.500 1.3882 0.03527 0.03199 -0.0186 0.0020 1.0000
12.750 1.3849 0.03770 0.03462 -0.0165 0.0020 1.0000
13.000 1.3744 0.04081 0.03792 -0.0152 0.0019 1.0000
13.250 1.3606 0.04538 0.04268 -0.0167 0.0019 1.0000
13.500 1.3437 0.05240 0.04991 -0.0221 0.0019 1.0000
13.750 1.3216 0.06263 0.06036 -0.0309 0.0020 1.0000
14.000 1.2905 0.07491 0.07282 -0.0395 0.0020 1.0000
14.250 1.2535 0.08738 0.08541 -0.0466 0.0020 1.0000
14.500 1.2145 0.09982 0.09795 -0.0529 0.0021 1.0000
14.750 1.1749 0.11250 0.11071 -0.0591 0.0021 1.0000
15.000 1.1379 0.12505 0.12333 -0.0652 0.0021 1.0000
15.250 1.1044 0.13759 0.13594 -0.0713 0.0022 1.0000
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Polar data table (+)
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