Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dayton-Wright 6 (daytonwright6-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.77 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-daytonwright6-il-1000000.txt Download as CSV file: xf-daytonwright6-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Dayton-Wright 6
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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1346 0.08563 0.08399 -0.0744 0.9810 0.0279
-12.000 -0.1250 0.08276 0.08112 -0.0757 0.9757 0.0281
-11.750 -0.1153 0.07922 0.07758 -0.0779 0.9722 0.0283
-11.500 -0.4631 0.03071 0.02807 -0.1158 0.9493 0.0254
-11.250 -0.4454 0.02699 0.02396 -0.1181 0.9404 0.0258
-11.000 -0.4178 0.02421 0.02082 -0.1208 0.9306 0.0261
-10.750 -0.3911 0.02212 0.01843 -0.1223 0.9186 0.0263
-10.500 -0.3658 0.02054 0.01657 -0.1229 0.9054 0.0265
-10.250 -0.3428 0.01946 0.01525 -0.1226 0.8918 0.0267
-10.000 -0.3211 0.01869 0.01427 -0.1216 0.8799 0.0269
-9.750 -0.3006 0.01817 0.01358 -0.1202 0.8694 0.0271
-9.500 -0.2783 0.01799 0.01327 -0.1191 0.8609 0.0273
-9.250 -0.2662 0.01588 0.01088 -0.1167 0.8520 0.0277
-9.000 -0.2464 0.01494 0.00983 -0.1152 0.8449 0.0280
-8.750 -0.2251 0.01430 0.00910 -0.1139 0.8378 0.0282
-8.500 -0.2025 0.01377 0.00848 -0.1128 0.8313 0.0284
-8.250 -0.1805 0.01325 0.00790 -0.1115 0.8250 0.0287
-8.000 -0.1575 0.01284 0.00742 -0.1104 0.8180 0.0289
-7.750 -0.1347 0.01242 0.00692 -0.1093 0.8115 0.0292
-7.500 -0.1119 0.01203 0.00647 -0.1081 0.8039 0.0295
-7.250 -0.0890 0.01167 0.00604 -0.1069 0.7956 0.0297
-7.000 -0.0663 0.01134 0.00565 -0.1056 0.7864 0.0300
-6.750 -0.0432 0.01103 0.00528 -0.1044 0.7780 0.0304
-6.500 -0.0201 0.01073 0.00492 -0.1032 0.7690 0.0308
-6.250 0.0030 0.01047 0.00461 -0.1021 0.7593 0.0311
-6.000 0.0260 0.01028 0.00435 -0.1008 0.7477 0.0316
-5.750 0.0487 0.01010 0.00411 -0.0995 0.7332 0.0319
-5.500 0.0707 0.00994 0.00386 -0.0981 0.7150 0.0321
-5.250 0.0898 0.00967 0.00347 -0.0960 0.6884 0.0326
-5.000 0.1081 0.00953 0.00317 -0.0938 0.6581 0.0331
-4.750 0.1273 0.00944 0.00296 -0.0919 0.6310 0.0338
-4.500 0.1481 0.00939 0.00280 -0.0902 0.6086 0.0344
-4.250 0.1698 0.00935 0.00266 -0.0888 0.5904 0.0350
-4.000 0.1922 0.00930 0.00254 -0.0875 0.5755 0.0358
-3.750 0.2153 0.00925 0.00242 -0.0863 0.5638 0.0367
-3.250 0.2622 0.00912 0.00220 -0.0842 0.5446 0.0397
-3.000 0.2849 0.00908 0.00212 -0.0830 0.5356 0.0424
-2.750 0.3085 0.00895 0.00204 -0.0820 0.5281 0.0545
-2.500 0.3307 0.00886 0.00202 -0.0807 0.5206 0.0820
-2.250 0.3546 0.00879 0.00199 -0.0798 0.5140 0.0993
-2.000 0.3782 0.00876 0.00198 -0.0788 0.5074 0.1134
-1.750 0.4014 0.00875 0.00198 -0.0778 0.5011 0.1272
-1.500 0.4256 0.00870 0.00197 -0.0770 0.4949 0.1444
-1.250 0.4484 0.00868 0.00198 -0.0759 0.4882 0.1646
-1.000 0.4719 0.00865 0.00199 -0.0749 0.4822 0.1868
-0.750 0.4948 0.00858 0.00201 -0.0739 0.4759 0.2179
-0.500 0.5160 0.00854 0.00204 -0.0725 0.4695 0.2617
-0.250 0.5377 0.00839 0.00208 -0.0713 0.4641 0.3304
0.000 0.5569 0.00819 0.00211 -0.0695 0.4577 0.4228
0.500 0.7203 0.00773 0.00296 -0.0938 0.4359 0.9814
0.750 0.7645 0.00789 0.00307 -0.0975 0.4274 0.9853
1.000 0.8076 0.00808 0.00318 -0.1010 0.4184 0.9895
1.250 0.8510 0.00827 0.00330 -0.1045 0.4087 0.9938
1.500 0.8989 0.00837 0.00333 -0.1091 0.3987 0.9967
2.000 0.9686 0.00859 0.00343 -0.1127 0.3805 1.0000
2.250 0.9869 0.00874 0.00353 -0.1109 0.3727 1.0000
2.500 1.0071 0.00885 0.00361 -0.1095 0.3659 1.0000
2.750 1.0260 0.00900 0.00372 -0.1078 0.3593 1.0000
3.000 1.0456 0.00913 0.00383 -0.1063 0.3535 1.0000
3.250 1.0652 0.00926 0.00394 -0.1048 0.3476 1.0000
3.500 1.0833 0.00945 0.00408 -0.1030 0.3413 1.0000
3.750 1.1034 0.00956 0.00420 -0.1016 0.3371 1.0000
4.000 1.1227 0.00971 0.00432 -0.1000 0.3322 1.0000
4.250 1.1402 0.00991 0.00448 -0.0981 0.3263 1.0000
4.500 1.1596 0.01004 0.00462 -0.0966 0.3218 1.0000
4.750 1.1785 0.01018 0.00476 -0.0950 0.3174 1.0000
5.000 1.1936 0.01039 0.00493 -0.0926 0.3113 1.0000
5.250 1.2094 0.01052 0.00507 -0.0903 0.3069 1.0000
5.500 1.2257 0.01064 0.00521 -0.0882 0.3029 1.0000
5.750 1.2414 0.01081 0.00537 -0.0860 0.2988 1.0000
6.000 1.2559 0.01104 0.00557 -0.0835 0.2932 1.0000
6.250 1.2744 0.01116 0.00572 -0.0820 0.2890 1.0000
6.500 1.2912 0.01135 0.00590 -0.0801 0.2838 1.0000
6.750 1.3064 0.01161 0.00613 -0.0779 0.2786 1.0000
7.000 1.3252 0.01176 0.00631 -0.0765 0.2740 1.0000
7.250 1.3417 0.01200 0.00654 -0.0747 0.2673 1.0000
7.500 1.3583 0.01226 0.00680 -0.0729 0.2618 1.0000
7.750 1.3758 0.01250 0.00703 -0.0713 0.2545 1.0000
8.000 1.3910 0.01283 0.00733 -0.0694 0.2461 1.0000
8.250 1.4054 0.01322 0.00768 -0.0674 0.2345 1.0000
8.500 1.4176 0.01370 0.00809 -0.0651 0.2192 1.0000
8.750 1.4279 0.01429 0.00859 -0.0626 0.2005 1.0000
9.000 1.4288 0.01533 0.00942 -0.0586 0.1695 1.0000
9.250 1.4230 0.01674 0.01060 -0.0539 0.1347 1.0000
9.500 1.4080 0.01873 0.01231 -0.0482 0.0918 1.0000
9.750 1.3888 0.02117 0.01449 -0.0426 0.0511 1.0000
10.000 1.3740 0.02360 0.01679 -0.0381 0.0215 1.0000
10.250 1.3787 0.02493 0.01815 -0.0361 0.0181 1.0000
10.500 1.3866 0.02611 0.01937 -0.0346 0.0170 1.0000
10.750 1.3926 0.02747 0.02078 -0.0330 0.0161 1.0000
11.000 1.3968 0.02902 0.02239 -0.0314 0.0152 1.0000
11.250 1.4025 0.03051 0.02394 -0.0301 0.0150 1.0000
11.500 1.4083 0.03205 0.02555 -0.0289 0.0145 1.0000
11.750 1.4130 0.03376 0.02733 -0.0278 0.0142 1.0000
12.000 1.4161 0.03567 0.02930 -0.0268 0.0137 1.0000
12.250 1.4187 0.03771 0.03141 -0.0259 0.0133 1.0000
12.500 1.4172 0.04025 0.03403 -0.0250 0.0130 1.0000
12.750 1.4137 0.04314 0.03701 -0.0244 0.0126 1.0000
13.000 1.4060 0.04663 0.04061 -0.0238 0.0123 1.0000
13.250 1.4038 0.04964 0.04371 -0.0236 0.0122 1.0000
13.500 1.4040 0.05246 0.04660 -0.0236 0.0120 1.0000
13.750 1.4024 0.05552 0.04974 -0.0237 0.0118 1.0000
14.000 1.3969 0.05911 0.05342 -0.0238 0.0116 1.0000
14.250 1.3899 0.06294 0.05735 -0.0240 0.0116 1.0000
14.500 1.3829 0.06684 0.06134 -0.0244 0.0114 1.0000
14.750 1.3757 0.07079 0.06538 -0.0248 0.0113 1.0000
15.000 1.3681 0.07488 0.06956 -0.0253 0.0110 1.0000
15.250 1.3596 0.07916 0.07393 -0.0260 0.0110 1.0000
15.500 1.3500 0.08365 0.07851 -0.0267 0.0109 1.0000
15.750 1.3405 0.08817 0.08312 -0.0276 0.0108 1.0000
16.000 1.3309 0.09279 0.08783 -0.0285 0.0107 1.0000
16.250 1.3232 0.09720 0.09231 -0.0295 0.0105 1.0000
16.500 1.3112 0.10229 0.09750 -0.0307 0.0105 1.0000
16.750 1.3003 0.10726 0.10254 -0.0319 0.0102 1.0000
17.000 1.2909 0.11209 0.10745 -0.0333 0.0102 1.0000
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