ARA-D 20% AIRFOIL (arad20-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 20% AIRFOIL (arad20-il) Reynolds number: 50,000 Max Cl/Cd: 18.2 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad20-il-50000-n5.txt Download as CSV file: xf-arad20-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 20% AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5631 0.09508 0.08768 -0.0258 1.0000 0.0773
-11.750 -0.6338 0.07925 0.07156 -0.0368 1.0000 0.0766
-11.500 -0.6810 0.07053 0.06255 -0.0413 1.0000 0.0764
-11.250 -0.7176 0.06490 0.05663 -0.0415 1.0000 0.0766
-11.000 -0.7462 0.06031 0.05167 -0.0400 1.0000 0.0773
-10.750 -0.7417 0.05794 0.04927 -0.0391 1.0000 0.0789
-10.500 -0.7351 0.05569 0.04696 -0.0382 1.0000 0.0808
-10.250 -0.7336 0.05267 0.04366 -0.0371 1.0000 0.0830
-10.000 -0.7291 0.04963 0.04028 -0.0361 1.0000 0.0854
-9.750 -0.7113 0.04812 0.03885 -0.0356 1.0000 0.0880
-9.500 -0.6980 0.04588 0.03638 -0.0349 1.0000 0.0914
-9.250 -0.6804 0.04405 0.03450 -0.0344 1.0000 0.0946
-9.000 -0.6613 0.04253 0.03297 -0.0340 1.0000 0.0985
-8.750 -0.6426 0.04080 0.03114 -0.0336 1.0000 0.1027
-8.500 -0.6084 0.03935 0.02969 -0.0359 0.9435 0.1082
-8.250 -0.5713 0.03788 0.02807 -0.0381 0.8758 0.1146
-8.000 -0.5429 0.03664 0.02647 -0.0382 0.8236 0.1217
-7.750 -0.5194 0.03584 0.02558 -0.0373 0.7846 0.1278
-7.500 -0.4967 0.03497 0.02447 -0.0362 0.7551 0.1351
-7.250 -0.4735 0.03418 0.02344 -0.0352 0.7316 0.1439
-7.000 -0.4499 0.03345 0.02267 -0.0344 0.7119 0.1527
-6.750 -0.4258 0.03273 0.02184 -0.0337 0.6958 0.1634
-6.500 -0.4012 0.03205 0.02106 -0.0331 0.6813 0.1760
-6.250 -0.3760 0.03139 0.02036 -0.0327 0.6679 0.1907
-6.000 -0.3511 0.03078 0.01971 -0.0322 0.6564 0.2078
-5.750 -0.3252 0.03019 0.01917 -0.0321 0.6450 0.2282
-5.500 -0.2995 0.02967 0.01864 -0.0318 0.6350 0.2525
-5.250 -0.2735 0.02917 0.01823 -0.0316 0.6256 0.2801
-5.000 -0.2471 0.02874 0.01789 -0.0314 0.6158 0.3120
-4.750 -0.2212 0.02840 0.01762 -0.0310 0.6081 0.3465
-4.500 -0.1940 0.02812 0.01749 -0.0309 0.5992 0.3845
-4.250 -0.1676 0.02794 0.01740 -0.0305 0.5909 0.4239
-4.000 -0.1415 0.02785 0.01732 -0.0297 0.5841 0.4634
-3.750 -0.1148 0.02783 0.01748 -0.0292 0.5757 0.5013
-3.500 -0.0884 0.02787 0.01759 -0.0284 0.5682 0.5384
-3.250 -0.0625 0.02796 0.01763 -0.0274 0.5619 0.5749
-3.000 -0.0364 0.02814 0.01790 -0.0265 0.5544 0.6075
-2.750 -0.0102 0.02832 0.01811 -0.0256 0.5471 0.6398
-2.500 0.0154 0.02850 0.01823 -0.0243 0.5409 0.6703
-2.250 0.0405 0.02875 0.01844 -0.0229 0.5348 0.6979
-2.000 0.0657 0.02902 0.01877 -0.0219 0.5272 0.7248
-1.750 0.0906 0.02925 0.01894 -0.0205 0.5209 0.7509
-1.500 0.1155 0.02943 0.01900 -0.0190 0.5157 0.7763
-1.250 0.1405 0.02975 0.01933 -0.0181 0.5088 0.8009
-1.000 0.1658 0.03002 0.01959 -0.0171 0.5018 0.8249
-0.750 0.1920 0.03020 0.01966 -0.0161 0.4962 0.8486
-0.500 0.2197 0.03037 0.01966 -0.0154 0.4914 0.8720
-0.250 0.2495 0.03082 0.02019 -0.0160 0.4832 0.8942
0.000 0.2839 0.03110 0.02039 -0.0170 0.4766 0.9151
0.250 0.3230 0.03129 0.02039 -0.0189 0.4714 0.9347
0.500 0.3644 0.03189 0.02099 -0.0221 0.4636 0.9527
0.750 0.4089 0.03237 0.02141 -0.0259 0.4561 0.9689
1.000 0.4567 0.03261 0.02146 -0.0299 0.4505 0.9831
1.250 0.5017 0.03330 0.02214 -0.0343 0.4431 0.9978
1.500 0.5180 0.03376 0.02259 -0.0337 0.4369 1.0000
1.750 0.5326 0.03398 0.02269 -0.0322 0.4324 1.0000
2.000 0.5510 0.03411 0.02264 -0.0309 0.4288 1.0000
2.250 0.5673 0.03511 0.02368 -0.0304 0.4223 1.0000
2.500 0.5874 0.03592 0.02447 -0.0302 0.4160 1.0000
2.750 0.6120 0.03631 0.02474 -0.0301 0.4114 1.0000
3.000 0.6393 0.03651 0.02474 -0.0300 0.4080 1.0000
3.250 0.6551 0.03829 0.02669 -0.0302 0.4002 1.0000
3.500 0.6776 0.03914 0.02751 -0.0302 0.3946 1.0000
3.750 0.7047 0.03945 0.02769 -0.0302 0.3907 1.0000
4.000 0.7283 0.04026 0.02844 -0.0302 0.3864 1.0000
4.250 0.7382 0.04258 0.03095 -0.0300 0.3786 1.0000
4.500 0.7614 0.04330 0.03162 -0.0299 0.3741 1.0000
4.750 0.7903 0.04342 0.03160 -0.0298 0.3709 1.0000
5.000 0.7909 0.04656 0.03495 -0.0292 0.3636 1.0000
5.250 0.8000 0.04862 0.03708 -0.0287 0.3577 1.0000
5.500 0.8254 0.04902 0.03740 -0.0285 0.3543 1.0000
5.750 0.8580 0.04876 0.03701 -0.0285 0.3518 1.0000
6.000 0.7887 0.05811 0.04680 -0.0262 0.3397 1.0000
6.250 0.8102 0.05869 0.04733 -0.0257 0.3366 1.0000
6.500 0.8456 0.05809 0.04662 -0.0255 0.3346 1.0000
8.000 0.6869 0.09937 0.08834 -0.0338 0.2886 1.0000
8.250 0.7052 0.10065 0.08960 -0.0337 0.2858 1.0000
8.500 0.7295 0.10112 0.09003 -0.0332 0.2840 1.0000
8.750 0.6849 0.11137 0.10040 -0.0369 0.2750 1.0000
9.000 0.6969 0.11360 0.10262 -0.0372 0.2716 1.0000
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Polar data table (+)
Polar graphs
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