Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Davis AIRFOIL (davis-il) Reynolds number: 500,000 Max Cl/Cd: 91.33 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-davis-il-500000-n5.txt Download as CSV file: xf-davis-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Davis AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6090 0.06928 0.06691 -0.0558 1.0000 0.0062
-11.500 -0.6514 0.05976 0.05736 -0.0605 0.9994 0.0062
-11.250 -0.6832 0.04021 0.03746 -0.0862 0.9902 0.0060
-11.000 -0.6818 0.03432 0.03118 -0.0924 0.9828 0.0061
-10.750 -0.6719 0.03031 0.02677 -0.0953 0.9784 0.0061
-10.500 -0.6576 0.02799 0.02417 -0.0960 0.9740 0.0062
-10.250 -0.6432 0.02503 0.02089 -0.0968 0.9702 0.0064
-10.000 -0.6192 0.02329 0.01895 -0.0981 0.9683 0.0067
-9.750 -0.5993 0.02210 0.01759 -0.0977 0.9637 0.0068
-9.500 -0.5730 0.02099 0.01634 -0.0985 0.9608 0.0071
-9.250 -0.5443 0.01987 0.01506 -0.0997 0.9586 0.0074
-9.000 -0.5218 0.01884 0.01384 -0.0994 0.9535 0.0078
-8.750 -0.4955 0.01787 0.01271 -0.0997 0.9495 0.0081
-8.500 -0.4659 0.01704 0.01173 -0.1006 0.9469 0.0086
-8.250 -0.4439 0.01632 0.01088 -0.0998 0.9409 0.0090
-8.000 -0.4179 0.01536 0.00981 -0.1000 0.9367 0.0097
-7.750 -0.3917 0.01474 0.00909 -0.1000 0.9319 0.0103
-7.500 -0.3661 0.01420 0.00846 -0.0998 0.9260 0.0109
-7.250 -0.3370 0.01364 0.00778 -0.1003 0.9220 0.0117
-7.000 -0.3133 0.01317 0.00721 -0.0995 0.9151 0.0124
-6.750 -0.2859 0.01259 0.00655 -0.0996 0.9092 0.0138
-6.500 -0.2602 0.01224 0.00617 -0.0993 0.9012 0.0154
-6.250 -0.2319 0.01189 0.00575 -0.0994 0.8942 0.0171
-6.000 -0.2063 0.01159 0.00536 -0.0990 0.8856 0.0184
-5.750 -0.1794 0.01114 0.00485 -0.0989 0.8775 0.0211
-5.500 -0.1531 0.01090 0.00456 -0.0986 0.8671 0.0242
-5.250 -0.1262 0.01070 0.00426 -0.0983 0.8560 0.0263
-5.000 -0.0999 0.01039 0.00385 -0.0980 0.8439 0.0292
-4.750 -0.0738 0.01012 0.00350 -0.0976 0.8303 0.0327
-4.500 -0.0476 0.00994 0.00321 -0.0973 0.8163 0.0355
-4.250 -0.0217 0.00977 0.00294 -0.0968 0.8007 0.0395
-4.000 0.0037 0.00957 0.00269 -0.0962 0.7864 0.0468
-3.750 0.0280 0.00927 0.00244 -0.0956 0.7738 0.0794
-3.500 0.0532 0.00906 0.00229 -0.0951 0.7630 0.1100
-3.250 0.0790 0.00895 0.00218 -0.0947 0.7538 0.1307
-2.500 0.1570 0.00872 0.00187 -0.0935 0.7293 0.1727
-2.250 0.1829 0.00862 0.00181 -0.0931 0.7214 0.1931
-2.000 0.2090 0.00856 0.00176 -0.0928 0.7140 0.2132
-1.750 0.2352 0.00850 0.00171 -0.0924 0.7063 0.2332
-1.500 0.2612 0.00846 0.00167 -0.0920 0.6989 0.2515
-1.250 0.2870 0.00838 0.00163 -0.0916 0.6900 0.2730
-1.000 0.3124 0.00829 0.00160 -0.0912 0.6812 0.3031
-0.750 0.3375 0.00816 0.00160 -0.0906 0.6721 0.3477
-0.500 0.3629 0.00810 0.00159 -0.0901 0.6615 0.3809
-0.250 0.3877 0.00806 0.00158 -0.0895 0.6469 0.4113
0.000 0.4118 0.00804 0.00158 -0.0887 0.6284 0.4417
0.250 0.4351 0.00803 0.00157 -0.0878 0.6052 0.4759
0.500 0.4573 0.00805 0.00158 -0.0866 0.5810 0.5127
0.750 0.4794 0.00800 0.00162 -0.0855 0.5626 0.5653
1.000 0.4950 0.00760 0.00172 -0.0829 0.5488 0.7433
1.250 0.5162 0.00742 0.00185 -0.0812 0.5367 0.8676
1.500 0.5783 0.00755 0.00204 -0.0887 0.5233 0.9562
1.750 0.6238 0.00771 0.00214 -0.0927 0.5122 0.9785
2.000 0.6612 0.00787 0.00224 -0.0949 0.5013 0.9910
2.250 0.6982 0.00804 0.00235 -0.0971 0.4887 0.9999
2.500 0.7207 0.00817 0.00244 -0.0960 0.4772 1.0000
2.750 0.7429 0.00830 0.00253 -0.0949 0.4650 1.0000
3.000 0.7648 0.00844 0.00263 -0.0937 0.4507 1.0000
3.250 0.7860 0.00862 0.00274 -0.0924 0.4322 1.0000
3.500 0.8064 0.00883 0.00287 -0.0909 0.4078 1.0000
3.750 0.8257 0.00911 0.00302 -0.0893 0.3816 1.0000
4.000 0.8455 0.00939 0.00320 -0.0877 0.3626 1.0000
4.250 0.8660 0.00963 0.00340 -0.0863 0.3493 1.0000
4.500 0.8869 0.00987 0.00359 -0.0850 0.3390 1.0000
4.750 0.9080 0.01010 0.00380 -0.0837 0.3298 1.0000
5.000 0.9290 0.01035 0.00401 -0.0824 0.3194 1.0000
5.250 0.9495 0.01062 0.00425 -0.0811 0.3075 1.0000
5.750 0.9908 0.01115 0.00472 -0.0784 0.2826 1.0000
6.000 1.0111 0.01144 0.00495 -0.0771 0.2663 1.0000
6.250 1.0316 0.01171 0.00520 -0.0758 0.2507 1.0000
6.500 1.0502 0.01209 0.00548 -0.0742 0.2272 1.0000
6.750 1.0674 0.01253 0.00581 -0.0724 0.2022 1.0000
7.000 1.0718 0.01364 0.00647 -0.0684 0.1257 1.0000
7.250 1.0732 0.01486 0.00734 -0.0639 0.0657 1.0000
7.750 1.0926 0.01648 0.00869 -0.0579 0.0168 1.0000
8.000 1.1087 0.01695 0.00923 -0.0559 0.0144 1.0000
8.250 1.1243 0.01746 0.00979 -0.0540 0.0127 1.0000
8.500 1.1387 0.01805 0.01043 -0.0519 0.0114 1.0000
8.750 1.1511 0.01876 0.01121 -0.0496 0.0103 1.0000
9.000 1.1651 0.01938 0.01190 -0.0476 0.0098 1.0000
9.250 1.1784 0.02005 0.01265 -0.0455 0.0094 1.0000
9.500 1.1909 0.02077 0.01344 -0.0435 0.0088 1.0000
9.750 1.2028 0.02154 0.01429 -0.0414 0.0083 1.0000
10.000 1.2140 0.02237 0.01518 -0.0394 0.0078 1.0000
10.250 1.2222 0.02341 0.01627 -0.0371 0.0073 1.0000
10.500 1.2258 0.02478 0.01773 -0.0344 0.0070 1.0000
10.750 1.2357 0.02579 0.01883 -0.0325 0.0067 1.0000
11.000 1.2430 0.02702 0.02015 -0.0306 0.0065 1.0000
11.250 1.2487 0.02841 0.02162 -0.0286 0.0064 1.0000
11.500 1.2536 0.02993 0.02324 -0.0267 0.0061 1.0000
11.750 1.2588 0.03150 0.02490 -0.0251 0.0059 1.0000
12.000 1.2612 0.03337 0.02686 -0.0235 0.0058 1.0000
12.250 1.2646 0.03525 0.02883 -0.0222 0.0057 1.0000
12.500 1.2687 0.03714 0.03083 -0.0211 0.0054 1.0000
12.750 1.2700 0.03936 0.03314 -0.0200 0.0053 1.0000
13.000 1.2729 0.04151 0.03537 -0.0192 0.0052 1.0000
13.250 1.2721 0.04411 0.03805 -0.0185 0.0050 1.0000
13.500 1.2693 0.04701 0.04104 -0.0179 0.0048 1.0000
13.750 1.2650 0.05019 0.04432 -0.0174 0.0048 1.0000
14.000 1.2687 0.05262 0.04687 -0.0172 0.0046 1.0000
14.250 1.2635 0.05612 0.05050 -0.0170 0.0046 1.0000
14.500 1.2659 0.05887 0.05335 -0.0172 0.0044 1.0000
14.750 1.2638 0.06223 0.05684 -0.0175 0.0043 1.0000
15.000 1.2602 0.06584 0.06057 -0.0178 0.0043 1.0000
15.250 1.2576 0.06945 0.06430 -0.0184 0.0042 1.0000
15.500 1.2549 0.07314 0.06810 -0.0190 0.0041 1.0000
15.750 1.2521 0.07695 0.07203 -0.0199 0.0040 1.0000
16.000 1.2477 0.08101 0.07622 -0.0208 0.0040 1.0000
16.250 1.2429 0.08521 0.08054 -0.0219 0.0039 1.0000
16.500 1.2379 0.08957 0.08502 -0.0232 0.0038 1.0000
16.750 1.2340 0.09392 0.08950 -0.0247 0.0038 1.0000
17.000 1.2280 0.09862 0.09433 -0.0264 0.0037 1.0000
17.250 1.2204 0.10364 0.09948 -0.0281 0.0037 1.0000
17.500 1.2166 0.10828 0.10422 -0.0303 0.0036 1.0000
17.750 1.2091 0.11354 0.10961 -0.0324 0.0036 1.0000
18.000 1.2026 0.11876 0.11495 -0.0348 0.0036 1.0000
18.250 1.1955 0.12418 0.12050 -0.0374 0.0036 1.0000
18.500 1.1907 0.12926 0.12566 -0.0401 0.0035 1.0000
18.750 1.1799 0.13551 0.13207 -0.0431 0.0035 1.0000
19.000 1.1704 0.14171 0.13840 -0.0464 0.0035 1.0000
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