AG38 (ag38-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG38 (ag38-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.78 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag38-il-1000000-n5.txt Download as CSV file: xf-ag38-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG38
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 -0.5445 0.08955 0.08794 -0.0015 1.0000 0.0052
-8.000 -0.5560 0.01770 0.01379 -0.0430 0.9996 0.0057
-7.750 -0.5276 0.01578 0.01154 -0.0436 0.9981 0.0059
-7.500 -0.4981 0.01450 0.01001 -0.0442 0.9967 0.0061
-7.250 -0.4677 0.01353 0.00886 -0.0450 0.9954 0.0062
-7.000 -0.4367 0.01272 0.00791 -0.0458 0.9939 0.0063
-6.750 -0.4072 0.01181 0.00684 -0.0462 0.9910 0.0064
-6.500 -0.3776 0.01093 0.00583 -0.0467 0.9883 0.0067
-6.250 -0.3469 0.01044 0.00527 -0.0473 0.9857 0.0070
-6.000 -0.3157 0.01012 0.00493 -0.0480 0.9828 0.0074
-5.750 -0.2869 0.00979 0.00456 -0.0482 0.9784 0.0079
-5.500 -0.2573 0.00941 0.00413 -0.0485 0.9739 0.0084
-5.250 -0.2279 0.00904 0.00370 -0.0487 0.9688 0.0087
-5.000 -0.2000 0.00876 0.00337 -0.0485 0.9611 0.0091
-4.750 -0.1724 0.00838 0.00294 -0.0483 0.9529 0.0096
-4.500 -0.1454 0.00813 0.00266 -0.0480 0.9426 0.0104
-4.250 -0.1186 0.00794 0.00243 -0.0475 0.9297 0.0112
-4.000 -0.0921 0.00778 0.00221 -0.0470 0.9113 0.0121
-3.750 -0.0674 0.00772 0.00199 -0.0460 0.8551 0.0130
-3.500 -0.0416 0.00770 0.00177 -0.0453 0.8112 0.0150
-3.250 -0.0142 0.00769 0.00162 -0.0451 0.7807 0.0168
-3.000 0.0135 0.00766 0.00148 -0.0449 0.7524 0.0193
-2.750 0.0412 0.00764 0.00137 -0.0448 0.7213 0.0236
-2.500 0.0688 0.00765 0.00126 -0.0447 0.6739 0.0324
-2.250 0.0960 0.00775 0.00117 -0.0446 0.6100 0.0490
-2.000 0.1239 0.00771 0.00112 -0.0447 0.5797 0.0826
-1.750 0.1519 0.00758 0.00108 -0.0448 0.5590 0.1396
-1.500 0.1800 0.00740 0.00104 -0.0450 0.5421 0.2147
-1.250 0.2080 0.00709 0.00103 -0.0452 0.5278 0.3322
-1.000 0.2359 0.00669 0.00104 -0.0455 0.5146 0.4888
-0.750 0.2632 0.00623 0.00106 -0.0456 0.5018 0.6642
-0.500 0.2876 0.00573 0.00111 -0.0448 0.4900 0.8467
-0.250 0.3101 0.00550 0.00110 -0.0431 0.4781 0.9662
0.000 0.3436 0.00554 0.00108 -0.0444 0.4622 1.0000
0.250 0.3717 0.00565 0.00110 -0.0444 0.4428 1.0000
0.500 0.3997 0.00579 0.00113 -0.0445 0.4194 1.0000
0.750 0.4276 0.00596 0.00117 -0.0445 0.3925 1.0000
1.000 0.4553 0.00615 0.00125 -0.0446 0.3636 1.0000
1.250 0.4830 0.00636 0.00132 -0.0446 0.3346 1.0000
1.500 0.5106 0.00658 0.00142 -0.0447 0.3053 1.0000
1.750 0.5382 0.00681 0.00152 -0.0447 0.2769 1.0000
2.000 0.5657 0.00706 0.00165 -0.0448 0.2483 1.0000
2.250 0.5931 0.00733 0.00178 -0.0448 0.2185 1.0000
2.500 0.6206 0.00758 0.00192 -0.0449 0.1936 1.0000
2.750 0.6479 0.00785 0.00208 -0.0449 0.1687 1.0000
3.000 0.6753 0.00810 0.00225 -0.0450 0.1487 1.0000
3.250 0.7025 0.00838 0.00243 -0.0450 0.1282 1.0000
3.500 0.7296 0.00866 0.00263 -0.0450 0.1081 1.0000
3.750 0.7566 0.00898 0.00285 -0.0451 0.0889 1.0000
4.000 0.7836 0.00926 0.00308 -0.0451 0.0741 1.0000
4.250 0.8106 0.00955 0.00331 -0.0451 0.0624 1.0000
4.500 0.8375 0.00985 0.00356 -0.0451 0.0516 1.0000
4.750 0.8642 0.01016 0.00383 -0.0451 0.0427 1.0000
5.000 0.8911 0.01042 0.00409 -0.0451 0.0376 1.0000
5.250 0.9177 0.01074 0.00438 -0.0450 0.0322 1.0000
5.500 0.9444 0.01101 0.00467 -0.0450 0.0293 1.0000
5.750 0.9708 0.01134 0.00499 -0.0450 0.0256 1.0000
6.000 0.9971 0.01167 0.00533 -0.0449 0.0227 1.0000
6.250 1.0235 0.01196 0.00566 -0.0449 0.0212 1.0000
6.500 1.0495 0.01231 0.00601 -0.0448 0.0194 1.0000
6.750 1.0751 0.01273 0.00645 -0.0446 0.0172 1.0000
7.000 1.1009 0.01308 0.00684 -0.0445 0.0162 1.0000
7.250 1.1265 0.01343 0.00724 -0.0444 0.0154 1.0000
7.500 1.1518 0.01383 0.00767 -0.0442 0.0144 1.0000
7.750 1.1768 0.01426 0.00813 -0.0440 0.0134 1.0000
8.000 1.2010 0.01482 0.00874 -0.0437 0.0121 1.0000
8.250 1.2257 0.01524 0.00922 -0.0435 0.0116 1.0000
8.500 1.2501 0.01569 0.00973 -0.0432 0.0112 1.0000
8.750 1.2742 0.01616 0.01026 -0.0430 0.0106 1.0000
9.000 1.2980 0.01667 0.01082 -0.0426 0.0100 1.0000
9.250 1.3213 0.01721 0.01140 -0.0423 0.0094 1.0000
9.500 1.3434 0.01789 0.01215 -0.0418 0.0086 1.0000
9.750 1.3657 0.01852 0.01286 -0.0413 0.0082 1.0000
10.000 1.3880 0.01910 0.01353 -0.0408 0.0079 1.0000
10.250 1.4097 0.01973 0.01424 -0.0402 0.0076 1.0000
10.500 1.4309 0.02039 0.01497 -0.0396 0.0072 1.0000
10.750 1.4515 0.02108 0.01574 -0.0390 0.0069 1.0000
11.000 1.4713 0.02182 0.01655 -0.0382 0.0065 1.0000
11.250 1.4899 0.02266 0.01748 -0.0374 0.0062 1.0000
11.500 1.5055 0.02379 0.01871 -0.0361 0.0057 1.0000
11.750 1.5233 0.02459 0.01961 -0.0352 0.0056 1.0000
12.000 1.5397 0.02546 0.02059 -0.0341 0.0054 1.0000
12.250 1.5547 0.02641 0.02165 -0.0328 0.0052 1.0000
12.500 1.5677 0.02745 0.02279 -0.0313 0.0050 1.0000
12.750 1.5786 0.02854 0.02399 -0.0296 0.0048 1.0000
13.000 1.5850 0.02967 0.02522 -0.0271 0.0046 1.0000
13.250 1.5889 0.03096 0.02661 -0.0246 0.0044 1.0000
13.500 1.5914 0.03247 0.02824 -0.0224 0.0043 1.0000
13.750 1.5922 0.03427 0.03016 -0.0205 0.0042 1.0000
14.000 1.5904 0.03651 0.03252 -0.0190 0.0040 1.0000
14.250 1.5852 0.03942 0.03557 -0.0184 0.0039 1.0000
14.500 1.5764 0.04324 0.03956 -0.0188 0.0038 1.0000
14.750 1.5663 0.04778 0.04425 -0.0203 0.0037 1.0000
15.000 1.5572 0.05278 0.04941 -0.0228 0.0037 1.0000
15.250 1.5410 0.05945 0.05626 -0.0265 0.0036 1.0000
15.500 1.5196 0.06717 0.06416 -0.0308 0.0036 1.0000
15.750 1.4878 0.07684 0.07401 -0.0359 0.0037 1.0000
16.000 1.4477 0.08838 0.08573 -0.0418 0.0037 1.0000
16.250 1.4121 0.09919 0.09670 -0.0470 0.0038 1.0000
16.500 1.3712 0.11127 0.10894 -0.0528 0.0040 1.0000
16.750 1.3252 0.12489 0.12272 -0.0594 0.0042 1.0000
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Polar data table (+)
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