D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: D.G.A. 1138 (dga1138-il) Reynolds number: 50,000 Max Cl/Cd: 37.44 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dga1138-il-50000-n5.txt Download as CSV file: xf-dga1138-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4915 0.11322 0.10621 -0.0118 1.0000 0.1224
-9.500 -0.5010 0.11114 0.10425 -0.0153 1.0000 0.1239
-9.250 -0.5087 0.10852 0.10174 -0.0183 1.0000 0.1243
-8.750 -0.4965 0.09942 0.09272 -0.0192 1.0000 0.1255
-8.500 -0.4911 0.08940 0.08262 -0.0257 1.0000 0.0692
-8.250 -0.4855 0.08526 0.07850 -0.0264 1.0000 0.0664
-8.000 -0.4821 0.08057 0.07384 -0.0290 1.0000 0.0638
-7.750 -0.4785 0.07499 0.06823 -0.0331 1.0000 0.0611
-7.500 -0.4714 0.07063 0.06382 -0.0350 1.0000 0.0617
-7.250 -0.4627 0.06667 0.05979 -0.0362 1.0000 0.0639
-7.000 -0.4529 0.06200 0.05498 -0.0381 1.0000 0.0649
-6.750 -0.4414 0.05695 0.04973 -0.0397 1.0000 0.0646
-6.500 -0.4280 0.05178 0.04427 -0.0411 1.0000 0.0643
-6.250 -0.4127 0.04712 0.03923 -0.0418 1.0000 0.0659
-6.000 -0.3956 0.04212 0.03355 -0.0426 1.0000 0.0696
-5.750 -0.3768 0.03794 0.02871 -0.0424 1.0000 0.0708
-5.500 -0.3575 0.03511 0.02554 -0.0417 1.0000 0.0722
-5.250 -0.3369 0.03289 0.02300 -0.0409 1.0000 0.0742
-5.000 -0.3156 0.03125 0.02095 -0.0401 1.0000 0.0801
-4.750 -0.2923 0.02907 0.01815 -0.0393 1.0000 0.0826
-4.500 -0.2688 0.02733 0.01608 -0.0385 1.0000 0.0834
-4.250 -0.2454 0.02599 0.01451 -0.0376 1.0000 0.0847
-4.000 -0.2213 0.02488 0.01319 -0.0369 1.0000 0.0864
-3.750 -0.1965 0.02394 0.01201 -0.0362 1.0000 0.0888
-3.500 -0.1715 0.02316 0.01100 -0.0355 1.0000 0.0920
-3.250 -0.1457 0.02251 0.01013 -0.0349 1.0000 0.0962
-3.000 -0.1209 0.02200 0.00957 -0.0344 1.0000 0.1024
-2.750 -0.0963 0.02157 0.00907 -0.0339 1.0000 0.1143
-2.500 -0.0720 0.02120 0.00880 -0.0334 1.0000 0.1417
-2.250 -0.0475 0.02083 0.00856 -0.0330 1.0000 0.1880
-2.000 -0.0234 0.02058 0.00838 -0.0326 1.0000 0.2436
-1.750 0.0006 0.02031 0.00825 -0.0323 1.0000 0.2987
-1.500 0.0247 0.02000 0.00814 -0.0321 1.0000 0.3491
-1.250 0.0546 0.01816 0.00812 -0.0324 1.0000 1.0000
-1.000 0.0760 0.01843 0.00810 -0.0315 1.0000 1.0000
-0.750 0.0973 0.01872 0.00818 -0.0308 1.0000 1.0000
-0.500 0.1293 0.01903 0.00830 -0.0322 0.9953 1.0000
-0.250 0.1688 0.01935 0.00842 -0.0351 0.9866 1.0000
0.000 0.2079 0.01963 0.00858 -0.0379 0.9772 1.0000
0.250 0.2460 0.01990 0.00877 -0.0405 0.9670 1.0000
0.500 0.2834 0.02014 0.00896 -0.0429 0.9561 1.0000
0.750 0.3209 0.02038 0.00918 -0.0453 0.9447 1.0000
1.000 0.3602 0.02058 0.00942 -0.0479 0.9328 1.0000
1.250 0.4020 0.02069 0.00958 -0.0508 0.9193 1.0000
1.500 0.4455 0.02070 0.00971 -0.0538 0.9040 1.0000
1.750 0.4878 0.02060 0.00973 -0.0562 0.8861 1.0000
2.000 0.5292 0.02040 0.00966 -0.0581 0.8664 1.0000
2.250 0.5621 0.02025 0.00967 -0.0582 0.8415 1.0000
2.500 0.5937 0.02000 0.00955 -0.0578 0.8123 1.0000
2.750 0.6220 0.01981 0.00947 -0.0567 0.7797 1.0000
3.000 0.6498 0.01973 0.00956 -0.0557 0.7484 1.0000
3.250 0.6770 0.01973 0.00969 -0.0547 0.7160 1.0000
3.500 0.7027 0.01978 0.00985 -0.0534 0.6780 1.0000
3.750 0.7265 0.01990 0.01005 -0.0518 0.6285 1.0000
4.000 0.7511 0.02006 0.01001 -0.0497 0.5634 1.0000
4.250 0.7723 0.02073 0.01031 -0.0476 0.4966 1.0000
4.500 0.7910 0.02149 0.01101 -0.0457 0.4209 1.0000
4.750 0.8089 0.02240 0.01165 -0.0438 0.3456 1.0000
5.000 0.8280 0.02346 0.01255 -0.0424 0.3007 1.0000
5.250 0.8463 0.02464 0.01351 -0.0411 0.2552 1.0000
5.500 0.8633 0.02588 0.01446 -0.0399 0.2064 1.0000
5.750 0.8828 0.02699 0.01562 -0.0388 0.1752 1.0000
6.000 0.9020 0.02806 0.01669 -0.0378 0.1124 1.0000
6.250 0.9183 0.02987 0.01810 -0.0364 0.0677 1.0000
6.500 0.9356 0.03170 0.01999 -0.0347 0.0533 1.0000
6.750 0.9525 0.03342 0.02184 -0.0332 0.0457 1.0000
7.000 0.9700 0.03517 0.02378 -0.0317 0.0404 1.0000
7.250 0.9859 0.03705 0.02578 -0.0301 0.0373 1.0000
7.500 1.0018 0.03928 0.02817 -0.0285 0.0356 1.0000
7.750 1.0205 0.04171 0.03096 -0.0270 0.0344 1.0000
8.000 1.0379 0.04441 0.03404 -0.0255 0.0329 1.0000
8.250 1.0518 0.04720 0.03719 -0.0240 0.0312 1.0000
8.500 1.0621 0.05001 0.04030 -0.0223 0.0298 1.0000
8.750 1.0690 0.05306 0.04361 -0.0206 0.0287 1.0000
9.000 1.0725 0.05662 0.04746 -0.0186 0.0282 1.0000
9.250 1.0715 0.06041 0.05161 -0.0165 0.0280 1.0000
9.500 1.0652 0.06417 0.05569 -0.0142 0.0279 1.0000
9.750 1.0530 0.06780 0.05962 -0.0116 0.0279 1.0000
10.000 1.0384 0.07173 0.06381 -0.0098 0.0280 1.0000
10.250 1.0211 0.07612 0.06851 -0.0093 0.0281 1.0000
10.500 1.0005 0.08140 0.07406 -0.0103 0.0283 1.0000
10.750 0.9756 0.08836 0.08128 -0.0138 0.0287 1.0000
11.000 0.9460 0.09823 0.09136 -0.0205 0.0294 1.0000
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Polar data table (+)
Polar graphs
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