DU 86-137/25 AIRFOIL (du861372-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DU 86-137/25 AIRFOIL (du861372-il) Reynolds number: 1,000,000 Max Cl/Cd: 58.4 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du861372-il-1000000.txt Download as CSV file: xf-du861372-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: DU 86-137/25 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.8843 0.04044 0.03534 -0.0297 0.2973 0.0099
-10.750 -0.8717 0.03709 0.03197 -0.0293 0.2959 0.0101
-10.500 -0.8657 0.03445 0.02926 -0.0279 0.2953 0.0102
-10.250 -0.8638 0.03209 0.02678 -0.0256 0.2948 0.0103
-10.000 -0.8597 0.02994 0.02450 -0.0235 0.2944 0.0105
-9.750 -0.8538 0.02792 0.02234 -0.0214 0.2934 0.0108
-9.500 -0.8462 0.02607 0.02032 -0.0194 0.2931 0.0111
-9.250 -0.8369 0.02457 0.01862 -0.0174 0.2923 0.0115
-9.000 -0.8282 0.02382 0.01763 -0.0149 0.2918 0.0119
-8.750 -0.8190 0.02331 0.01683 -0.0123 0.2914 0.0121
-8.500 -0.8068 0.02227 0.01553 -0.0102 0.2910 0.0121
-8.250 -0.7927 0.02108 0.01408 -0.0085 0.2905 0.0122
-8.000 -0.7765 0.01996 0.01272 -0.0071 0.2897 0.0122
-7.750 -0.7573 0.01898 0.01152 -0.0062 0.2892 0.0122
-7.500 -0.7352 0.01770 0.01013 -0.0057 0.2857 0.0122
-7.250 -0.7129 0.01674 0.00904 -0.0053 0.2850 0.0123
-7.000 -0.6901 0.01587 0.00803 -0.0049 0.2844 0.0123
-6.750 -0.6664 0.01510 0.00716 -0.0047 0.2837 0.0123
-6.500 -0.6422 0.01439 0.00636 -0.0045 0.2834 0.0123
-5.750 -0.5724 0.02265 0.01431 -0.0067 0.2801 0.0128
-5.500 -0.5441 0.02168 0.01337 -0.0071 0.2801 0.0129
-5.250 -0.5162 0.02077 0.01250 -0.0073 0.2800 0.0132
-5.000 -0.4895 0.02003 0.01178 -0.0074 0.2798 0.0136
-4.750 -0.4631 0.01925 0.01105 -0.0073 0.2791 0.0140
-4.500 -0.4376 0.01887 0.01065 -0.0071 0.2788 0.0144
-4.250 -0.4137 0.01895 0.01061 -0.0066 0.2785 0.0148
-4.000 -0.3895 0.01912 0.01067 -0.0061 0.2784 0.0150
-3.750 -0.3643 0.01910 0.01057 -0.0058 0.2783 0.0150
-3.500 -0.3384 0.01889 0.01033 -0.0057 0.2782 0.0151
-3.250 -0.3121 0.01863 0.01007 -0.0057 0.2781 0.0151
-3.000 -0.2855 0.01716 0.00883 -0.0058 0.2775 0.0154
-2.750 -0.2627 0.01640 0.00819 -0.0052 0.2767 0.0156
-2.500 -0.2402 0.01592 0.00777 -0.0045 0.2759 0.0158
-2.250 -0.2171 0.01559 0.00745 -0.0040 0.2757 0.0161
-2.000 -0.1932 0.01532 0.00720 -0.0036 0.2755 0.0165
-1.750 -0.1685 0.01516 0.00704 -0.0033 0.2751 0.0169
-1.500 -0.1423 0.01516 0.00702 -0.0032 0.2745 0.0176
-1.250 -0.1129 0.01550 0.00729 -0.0036 0.2743 0.0180
-1.000 -0.0924 0.01483 0.00669 -0.0027 0.2743 0.0187
-0.750 -0.0678 0.01458 0.00645 -0.0025 0.2741 0.0197
-0.500 -0.0392 0.01482 0.00666 -0.0027 0.2740 0.0212
-0.250 -0.0160 0.01442 0.00626 -0.0023 0.2736 0.0237
0.000 0.0098 0.01440 0.00620 -0.0022 0.2730 0.0268
0.250 0.1190 0.00777 0.00009 -0.0190 0.2723 0.0176
1.250 0.6913 0.02422 0.01883 -0.0276 0.2500 0.3772
1.500 0.1734 0.01639 0.00805 -0.0034 0.2708 0.0269
1.750 0.2010 0.01609 0.00781 -0.0035 0.2706 0.0258
2.000 0.2280 0.01506 0.00690 -0.0032 0.2642 0.0275
2.250 0.2537 0.01528 0.00719 -0.0031 0.2530 0.0268
2.500 0.2794 0.01532 0.00730 -0.0030 0.2453 0.0260
2.750 0.3059 0.01522 0.00726 -0.0029 0.2415 0.0256
3.000 0.3324 0.01527 0.00736 -0.0029 0.2395 0.0255
3.250 0.3586 0.01538 0.00752 -0.0028 0.2378 0.0283
3.500 0.3844 0.01526 0.00755 -0.0027 0.2349 0.0730
3.750 0.3990 0.01279 0.00700 -0.0014 0.2311 0.7108
4.000 0.4250 0.01263 0.00702 -0.0010 0.2282 0.7451
4.250 0.4510 0.01252 0.00703 -0.0005 0.2259 0.7686
4.500 0.4801 0.01186 0.00656 -0.0006 0.2235 0.7739
4.750 0.5069 0.01230 0.00696 -0.0007 0.2104 0.7787
5.000 0.5482 0.01073 0.00536 -0.0024 0.1721 0.7832
5.250 0.5746 0.01090 0.00542 -0.0023 0.1514 0.7888
5.500 0.5986 0.01121 0.00569 -0.0019 0.1358 0.7932
5.750 0.6217 0.01163 0.00596 -0.0014 0.1119 0.7962
6.000 0.6455 0.01200 0.00619 -0.0011 0.0908 0.7982
6.250 0.6701 0.01232 0.00642 -0.0008 0.0762 0.8001
6.500 0.6950 0.01262 0.00664 -0.0006 0.0648 0.8017
6.750 0.7198 0.01294 0.00688 -0.0004 0.0549 0.8031
7.000 0.7446 0.01316 0.00710 -0.0002 0.0485 0.8054
7.250 0.7687 0.01348 0.00737 0.0002 0.0411 0.8075
7.500 0.7929 0.01378 0.00765 0.0006 0.0362 0.8094
7.750 0.8167 0.01413 0.00799 0.0010 0.0317 0.8113
8.000 0.8407 0.01443 0.00830 0.0013 0.0288 0.8132
8.250 0.8625 0.01494 0.00879 0.0021 0.0250 0.8153
8.500 0.8866 0.01523 0.00911 0.0024 0.0239 0.8173
8.750 0.9099 0.01558 0.00948 0.0028 0.0224 0.8191
9.000 0.9323 0.01598 0.00988 0.0034 0.0211 0.8209
9.250 0.9496 0.01666 0.01062 0.0048 0.0192 0.8233
9.500 0.9711 0.01704 0.01106 0.0055 0.0187 0.8256
9.750 0.9932 0.01740 0.01146 0.0061 0.0181 0.8278
10.000 1.0136 0.01784 0.01195 0.0069 0.0174 0.8302
10.250 1.0339 0.01830 0.01245 0.0078 0.0167 0.8324
10.500 1.0532 0.01880 0.01298 0.0087 0.0162 0.8346
10.750 1.0716 0.01935 0.01355 0.0098 0.0155 0.8365
11.000 1.0794 0.02009 0.01437 0.0126 0.0148 0.8397
11.250 1.0757 0.02119 0.01562 0.0171 0.0143 0.8435
11.500 1.0964 0.02158 0.01605 0.0178 0.0140 0.8464
11.750 1.1122 0.02217 0.01670 0.0191 0.0138 0.8494
12.000 1.1277 0.02280 0.01739 0.0203 0.0134 0.8523
12.250 1.1401 0.02355 0.01823 0.0219 0.0131 0.8557
12.500 1.1545 0.02424 0.01899 0.0231 0.0127 0.8594
12.750 1.1680 0.02500 0.01982 0.0244 0.0124 0.8635
13.000 1.1826 0.02576 0.02064 0.0255 0.0121 0.8676
13.250 1.1972 0.02654 0.02147 0.0265 0.0117 0.8720
13.500 1.2063 0.02755 0.02258 0.0280 0.0114 0.8774
13.750 1.2098 0.02891 0.02404 0.0298 0.0112 0.8840
14.000 1.2044 0.03080 0.02610 0.0322 0.0109 0.8933
14.250 1.1908 0.03333 0.02887 0.0350 0.0105 0.9086
14.500 1.2098 0.03395 0.02966 0.0352 0.0104 0.9395
14.750 1.2365 0.03521 0.03105 0.0328 0.0102 1.0000
15.000 1.2441 0.03674 0.03268 0.0335 0.0100 1.0000
15.250 1.2554 0.03804 0.03405 0.0339 0.0098 1.0000
15.500 1.2583 0.03997 0.03610 0.0346 0.0096 1.0000
15.750 1.2653 0.04164 0.03785 0.0351 0.0093 1.0000
16.000 1.2678 0.04369 0.04000 0.0355 0.0092 1.0000
16.250 1.2708 0.04577 0.04216 0.0358 0.0090 1.0000
16.500 1.2694 0.04830 0.04479 0.0360 0.0089 1.0000
16.750 1.2635 0.05138 0.04800 0.0359 0.0088 1.0000
17.000 1.2559 0.05481 0.05154 0.0355 0.0087 1.0000
17.250 1.2552 0.05770 0.05450 0.0348 0.0085 1.0000
17.500 1.2391 0.06263 0.05957 0.0333 0.0084 1.0000
17.750 1.2129 0.06947 0.06658 0.0304 0.0085 1.0000
18.000 1.1654 0.08096 0.07831 0.0242 0.0086 1.0000
18.250 1.0810 0.10151 0.09919 0.0115 0.0090 1.0000
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