Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Davis AIRFOIL (davis-il) Reynolds number: 1,000,000 Max Cl/Cd: 120.76 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-davis-il-1000000.txt Download as CSV file: xf-davis-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.3921 0.11935 0.11768 -0.0365 1.0000 0.0128
-11.750 -0.3956 0.11471 0.11306 -0.0373 1.0000 0.0128
-11.500 -0.7514 0.03595 0.03365 -0.0862 0.9941 0.0080
-11.250 -0.7389 0.03277 0.03026 -0.0890 0.9897 0.0082
-11.000 -0.7260 0.02909 0.02627 -0.0918 0.9863 0.0083
-10.750 -0.7049 0.02642 0.02332 -0.0940 0.9845 0.0085
-10.500 -0.6838 0.02459 0.02129 -0.0949 0.9818 0.0087
-10.250 -0.6667 0.02252 0.01896 -0.0948 0.9775 0.0089
-10.000 -0.6412 0.02099 0.01722 -0.0958 0.9753 0.0091
-9.750 -0.6124 0.01985 0.01591 -0.0970 0.9738 0.0094
-9.500 -0.5817 0.01897 0.01490 -0.0983 0.9727 0.0096
-9.250 -0.5571 0.01632 0.01193 -0.0995 0.9713 0.0102
-9.000 -0.5312 0.01564 0.01118 -0.0996 0.9682 0.0106
-8.750 -0.5043 0.01524 0.01075 -0.0997 0.9646 0.0110
-8.500 -0.4746 0.01463 0.01005 -0.1005 0.9621 0.0115
-8.250 -0.4436 0.01416 0.00952 -0.1014 0.9600 0.0122
-8.000 -0.4128 0.01357 0.00884 -0.1023 0.9579 0.0126
-7.750 -0.3908 0.01262 0.00775 -0.1014 0.9530 0.0133
-7.500 -0.3659 0.01200 0.00708 -0.1010 0.9480 0.0141
-7.250 -0.3363 0.01161 0.00665 -0.1015 0.9442 0.0148
-7.000 -0.3097 0.01127 0.00626 -0.1013 0.9391 0.0157
-6.750 -0.2841 0.01098 0.00592 -0.1009 0.9331 0.0165
-6.500 -0.2566 0.01039 0.00523 -0.1009 0.9282 0.0178
-6.250 -0.2329 0.01009 0.00492 -0.1001 0.9208 0.0190
-6.000 -0.2049 0.00984 0.00463 -0.1001 0.9147 0.0205
-5.750 -0.1793 0.00964 0.00438 -0.0996 0.9064 0.0217
-5.500 -0.1538 0.00917 0.00381 -0.0991 0.8975 0.0234
-5.250 -0.1285 0.00889 0.00348 -0.0985 0.8859 0.0257
-5.000 -0.1027 0.00869 0.00323 -0.0980 0.8741 0.0278
-4.750 -0.0764 0.00856 0.00303 -0.0976 0.8622 0.0289
-4.500 -0.0518 0.00820 0.00258 -0.0969 0.8486 0.0328
-4.250 -0.0264 0.00803 0.00233 -0.0963 0.8333 0.0360
-4.000 -0.0010 0.00790 0.00211 -0.0956 0.8171 0.0393
-3.750 0.0234 0.00766 0.00188 -0.0949 0.8021 0.0548
-3.500 0.0465 0.00726 0.00169 -0.0940 0.7891 0.1183
-3.250 0.0720 0.00717 0.00161 -0.0935 0.7778 0.1403
-3.000 0.0975 0.00710 0.00152 -0.0930 0.7671 0.1571
-2.750 0.1232 0.00702 0.00144 -0.0925 0.7566 0.1736
-2.500 0.1490 0.00693 0.00138 -0.0921 0.7480 0.1949
-2.250 0.1747 0.00685 0.00134 -0.0917 0.7399 0.2245
-2.000 0.2012 0.00678 0.00130 -0.0914 0.7329 0.2453
-1.750 0.2273 0.00674 0.00127 -0.0910 0.7253 0.2628
-1.500 0.2536 0.00668 0.00123 -0.0906 0.7174 0.2809
-1.250 0.2793 0.00663 0.00120 -0.0902 0.7095 0.3055
-1.000 0.3046 0.00647 0.00120 -0.0897 0.7008 0.3584
-0.750 0.3295 0.00637 0.00120 -0.0891 0.6913 0.4079
-0.500 0.3548 0.00629 0.00120 -0.0885 0.6810 0.4468
-0.250 0.3804 0.00621 0.00119 -0.0880 0.6708 0.4841
0.000 0.4052 0.00613 0.00119 -0.0874 0.6595 0.5248
0.250 0.4285 0.00596 0.00119 -0.0865 0.6474 0.5945
0.500 0.4456 0.00554 0.00124 -0.0842 0.6327 0.7628
0.750 0.4650 0.00535 0.00130 -0.0821 0.6136 0.8687
1.000 0.5012 0.00540 0.00141 -0.0838 0.5901 0.9405
1.250 0.5493 0.00559 0.00150 -0.0883 0.5673 0.9652
1.500 0.5903 0.00578 0.00160 -0.0913 0.5504 0.9776
1.750 0.6297 0.00596 0.00170 -0.0939 0.5368 0.9878
2.000 0.6670 0.00611 0.00179 -0.0961 0.5250 0.9939
2.500 0.7423 0.00639 0.00194 -0.1007 0.5011 1.0000
2.750 0.7643 0.00649 0.00201 -0.0995 0.4901 1.0000
3.000 0.7864 0.00659 0.00209 -0.0983 0.4785 1.0000
3.250 0.8082 0.00672 0.00217 -0.0970 0.4649 1.0000
3.500 0.8296 0.00687 0.00226 -0.0957 0.4469 1.0000
3.750 0.8501 0.00707 0.00236 -0.0942 0.4214 1.0000
4.000 0.8680 0.00740 0.00252 -0.0923 0.3842 1.0000
4.250 0.8860 0.00774 0.00271 -0.0904 0.3557 1.0000
4.500 0.9054 0.00803 0.00291 -0.0887 0.3350 1.0000
4.750 0.9262 0.00826 0.00308 -0.0874 0.3226 1.0000
5.000 0.9471 0.00849 0.00326 -0.0860 0.3110 1.0000
5.250 0.9691 0.00867 0.00342 -0.0849 0.3013 1.0000
5.500 0.9910 0.00886 0.00359 -0.0837 0.2906 1.0000
5.750 1.0125 0.00907 0.00376 -0.0825 0.2799 1.0000
6.000 1.0338 0.00929 0.00394 -0.0813 0.2670 1.0000
6.250 1.0549 0.00952 0.00413 -0.0800 0.2513 1.0000
6.500 1.0740 0.00986 0.00436 -0.0784 0.2281 1.0000
6.750 1.0907 0.01032 0.00467 -0.0764 0.1984 1.0000
7.000 1.0884 0.01181 0.00555 -0.0711 0.0948 1.0000
7.250 1.0933 0.01293 0.00633 -0.0671 0.0374 1.0000
7.500 1.1039 0.01362 0.00690 -0.0639 0.0188 1.0000
7.750 1.1183 0.01409 0.00739 -0.0614 0.0159 1.0000
8.000 1.1347 0.01447 0.00781 -0.0593 0.0150 1.0000
8.250 1.1511 0.01486 0.00825 -0.0574 0.0142 1.0000
8.500 1.1659 0.01535 0.00878 -0.0551 0.0132 1.0000
8.750 1.1802 0.01590 0.00936 -0.0529 0.0125 1.0000
9.000 1.1900 0.01669 0.01024 -0.0499 0.0115 1.0000
9.250 1.2049 0.01722 0.01082 -0.0479 0.0112 1.0000
9.500 1.2198 0.01775 0.01139 -0.0460 0.0107 1.0000
9.750 1.2330 0.01838 0.01208 -0.0439 0.0103 1.0000
10.000 1.2453 0.01908 0.01282 -0.0417 0.0098 1.0000
10.250 1.2559 0.01988 0.01368 -0.0394 0.0095 1.0000
10.500 1.2653 0.02078 0.01463 -0.0371 0.0090 1.0000
10.750 1.2720 0.02188 0.01581 -0.0345 0.0089 1.0000
11.000 1.2670 0.02376 0.01781 -0.0308 0.0085 1.0000
11.250 1.2727 0.02507 0.01920 -0.0285 0.0083 1.0000
11.500 1.2811 0.02624 0.02044 -0.0267 0.0082 1.0000
11.750 1.2873 0.02764 0.02192 -0.0249 0.0081 1.0000
12.000 1.2996 0.02862 0.02295 -0.0238 0.0077 1.0000
12.250 1.3042 0.03026 0.02467 -0.0221 0.0076 1.0000
12.500 1.3108 0.03180 0.02628 -0.0208 0.0073 1.0000
12.750 1.3180 0.03335 0.02789 -0.0198 0.0070 1.0000
13.000 1.3199 0.03543 0.03007 -0.0185 0.0070 1.0000
13.250 1.3271 0.03710 0.03179 -0.0178 0.0067 1.0000
13.500 1.3276 0.03945 0.03422 -0.0167 0.0066 1.0000
13.750 1.3279 0.04189 0.03674 -0.0159 0.0066 1.0000
14.000 1.3284 0.04439 0.03932 -0.0152 0.0064 1.0000
14.250 1.3234 0.04750 0.04250 -0.0145 0.0062 1.0000
14.500 1.3159 0.05090 0.04601 -0.0136 0.0061 1.0000
14.750 1.3048 0.05466 0.04988 -0.0122 0.0060 1.0000
15.000 1.3064 0.05739 0.05271 -0.0124 0.0059 1.0000
15.250 1.3075 0.06028 0.05570 -0.0126 0.0059 1.0000
15.500 1.3088 0.06329 0.05882 -0.0132 0.0058 1.0000
15.750 1.3057 0.06672 0.06235 -0.0133 0.0058 1.0000
16.000 1.3050 0.07011 0.06585 -0.0141 0.0056 1.0000
16.250 1.3000 0.07390 0.06977 -0.0145 0.0056 1.0000
16.500 1.2954 0.07783 0.07382 -0.0153 0.0056 1.0000
16.750 1.2898 0.08198 0.07809 -0.0162 0.0055 1.0000
17.000 1.2841 0.08629 0.08252 -0.0175 0.0054 1.0000
17.250 1.2773 0.09075 0.08709 -0.0187 0.0055 1.0000
17.500 1.2649 0.09613 0.09262 -0.0201 0.0055 1.0000
17.750 1.2573 0.10111 0.09772 -0.0221 0.0054 1.0000
18.000 1.2504 0.10617 0.10289 -0.0244 0.0053 1.0000
18.250 1.2426 0.11141 0.10825 -0.0268 0.0052 1.0000
18.500 1.2266 0.11812 0.11513 -0.0296 0.0053 1.0000
18.750 1.2193 0.12365 0.12076 -0.0325 0.0051 1.0000
19.000 1.2001 0.13139 0.12868 -0.0363 0.0052 1.0000
19.250 1.1844 0.13876 0.13620 -0.0403 0.0052 1.0000
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