D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: D.G.A. 1138 (dga1138-il) Reynolds number: 50,000 Max Cl/Cd: 38.1 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dga1138-il-50000.txt Download as CSV file: xf-dga1138-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: D.G.A. 1138
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4972 0.10446 0.09766 -0.0096 1.0000 0.2183
-8.500 -0.4756 0.09864 0.09180 -0.0077 1.0000 0.2271
-8.250 -0.4981 0.09828 0.09161 -0.0121 1.0000 0.2331
-8.000 -0.4755 0.09237 0.08567 -0.0083 1.0000 0.2416
-7.750 -0.4813 0.08965 0.08305 -0.0107 1.0000 0.2495
-7.500 -0.4802 0.08688 0.08032 -0.0119 1.0000 0.2611
-7.250 -0.4686 0.08255 0.07602 -0.0098 1.0000 0.2714
-7.000 -0.4656 0.07937 0.07289 -0.0097 1.0000 0.2865
-6.750 -0.4695 0.07714 0.07070 -0.0121 1.0000 0.3048
-6.500 -0.4595 0.07298 0.06661 -0.0086 1.0000 0.3221
-6.250 -0.4523 0.06970 0.06336 -0.0066 1.0000 0.3410
-6.000 -0.4495 0.06671 0.06040 -0.0053 1.0000 0.3656
-5.750 -0.4450 0.06376 0.05750 -0.0024 1.0000 0.3946
-5.500 -0.4393 0.06085 0.05466 0.0021 1.0000 0.4282
-4.750 -0.3164 0.04161 0.03308 -0.0360 1.0000 0.1733
-4.500 -0.2901 0.03753 0.02830 -0.0368 1.0000 0.1599
-4.250 -0.2674 0.03471 0.02518 -0.0363 1.0000 0.1570
-4.000 -0.2429 0.03235 0.02229 -0.0360 1.0000 0.1591
-3.750 -0.2188 0.03031 0.01989 -0.0354 1.0000 0.1625
-3.500 -0.1937 0.02844 0.01767 -0.0349 1.0000 0.1641
-3.250 -0.1682 0.02687 0.01582 -0.0343 1.0000 0.1677
-3.000 -0.1412 0.02549 0.01404 -0.0338 1.0000 0.1738
-2.750 -0.1155 0.02437 0.01284 -0.0332 1.0000 0.1843
-2.500 -0.0896 0.02353 0.01186 -0.0326 1.0000 0.2052
-2.250 -0.0598 0.02245 0.01080 -0.0325 1.0000 0.2393
-2.000 -0.0275 0.02031 0.00928 -0.0330 1.0000 0.3684
-1.750 0.0095 0.01770 0.00860 -0.0339 1.0000 1.0000
-1.500 0.0324 0.01792 0.00835 -0.0331 1.0000 1.0000
-1.250 0.0542 0.01816 0.00822 -0.0322 1.0000 1.0000
-1.000 0.0757 0.01842 0.00822 -0.0314 1.0000 1.0000
-0.750 0.0970 0.01871 0.00829 -0.0306 1.0000 1.0000
-0.500 0.1181 0.01903 0.00843 -0.0299 1.0000 1.0000
-0.250 0.1390 0.01939 0.00863 -0.0292 1.0000 1.0000
0.000 0.1598 0.01978 0.00890 -0.0285 1.0000 1.0000
0.250 0.1803 0.02021 0.00924 -0.0280 1.0000 1.0000
0.500 0.2004 0.02069 0.00966 -0.0274 1.0000 1.0000
0.750 0.2202 0.02123 0.01016 -0.0270 1.0000 1.0000
1.000 0.2394 0.02184 0.01075 -0.0266 1.0000 1.0000
1.250 0.2578 0.02255 0.01146 -0.0263 1.0000 1.0000
1.500 0.2754 0.02337 0.01230 -0.0261 1.0000 1.0000
1.750 0.2918 0.02433 0.01330 -0.0260 1.0000 1.0000
2.000 0.3073 0.02542 0.01444 -0.0261 1.0000 1.0000
2.250 0.3648 0.02669 0.01583 -0.0339 0.9827 1.0000
2.500 0.4378 0.02744 0.01678 -0.0436 0.9511 1.0000
2.750 0.5136 0.02752 0.01717 -0.0523 0.9183 1.0000
3.000 0.5853 0.02704 0.01704 -0.0593 0.8877 1.0000
3.250 0.6399 0.02664 0.01702 -0.0630 0.8604 1.0000
3.500 0.6920 0.02580 0.01656 -0.0652 0.8307 1.0000
3.750 0.7336 0.02466 0.01580 -0.0644 0.7926 1.0000
4.000 0.7745 0.02284 0.01427 -0.0618 0.7438 1.0000
4.250 0.7986 0.02169 0.01317 -0.0566 0.6675 1.0000
4.500 0.8200 0.02152 0.01240 -0.0514 0.5535 1.0000
4.750 0.8410 0.02316 0.01338 -0.0487 0.4573 1.0000
5.000 0.8622 0.02433 0.01440 -0.0469 0.4020 1.0000
5.250 0.8831 0.02535 0.01523 -0.0451 0.3591 1.0000
5.500 0.8995 0.02637 0.01601 -0.0430 0.3112 1.0000
5.750 0.9140 0.02762 0.01703 -0.0409 0.2609 1.0000
6.000 0.9251 0.02952 0.01865 -0.0383 0.1977 1.0000
6.250 0.9420 0.03311 0.02185 -0.0361 0.1341 1.0000
6.500 0.9666 0.03585 0.02464 -0.0348 0.1141 1.0000
6.750 0.9891 0.03824 0.02717 -0.0336 0.1020 1.0000
7.000 1.0106 0.04069 0.02981 -0.0325 0.0932 1.0000
7.250 1.0309 0.04447 0.03401 -0.0311 0.0899 1.0000
7.500 1.0454 0.04864 0.03882 -0.0291 0.0885 1.0000
7.750 1.0551 0.05307 0.04382 -0.0269 0.0881 1.0000
8.000 1.0604 0.05769 0.04895 -0.0247 0.0884 1.0000
8.250 1.0610 0.06243 0.05420 -0.0225 0.0887 1.0000
8.500 1.0574 0.06723 0.05939 -0.0204 0.0893 1.0000
8.750 1.0509 0.07207 0.06453 -0.0185 0.0899 1.0000
9.000 1.0425 0.07693 0.06962 -0.0169 0.0905 1.0000
9.250 1.0344 0.08184 0.07468 -0.0157 0.0911 1.0000
9.500 0.9618 0.08960 0.08280 -0.0161 0.0992 1.0000
9.750 0.9427 0.09607 0.08930 -0.0184 0.1016 1.0000
10.000 0.9401 0.10176 0.09500 -0.0194 0.1035 1.0000
10.250 0.8895 0.11689 0.11004 -0.0333 0.1142 1.0000
10.500 0.7401 0.11442 0.10781 -0.0211 0.1149 1.0000
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Polar data table (+)
Polar graphs
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