Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dayton-Wright 6 (daytonwright6-il) Reynolds number: 200,000 Max Cl/Cd: 66.79 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-daytonwright6-il-200000.txt Download as CSV file: xf-daytonwright6-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.2789 0.12705 0.12344 -0.0376 1.0000 0.0589
-12.500 -0.3101 0.12583 0.12233 -0.0412 1.0000 0.0598
-12.250 -0.3145 0.12247 0.11903 -0.0404 1.0000 0.0601
-12.000 -0.3003 0.11930 0.11587 -0.0369 1.0000 0.0607
-11.750 -0.2984 0.11741 0.11402 -0.0344 1.0000 0.0612
-11.500 -0.3002 0.11594 0.11260 -0.0317 1.0000 0.0621
-11.250 -0.3061 0.11461 0.11132 -0.0294 1.0000 0.0628
-11.000 -0.3010 0.11198 0.10870 -0.0303 0.9987 0.0644
-10.750 -0.2870 0.10789 0.10461 -0.0357 0.9953 0.0672
-10.500 -0.3047 0.10252 0.09927 -0.0531 0.9865 0.0696
-10.250 -0.2768 0.09773 0.09447 -0.0499 0.9858 0.0707
-10.000 -0.2502 0.09456 0.09127 -0.0511 0.9837 0.0719
-9.750 -0.2334 0.09135 0.08806 -0.0535 0.9787 0.0734
-9.500 -0.2176 0.08768 0.08439 -0.0579 0.9739 0.0758
-9.250 -0.2217 0.08296 0.07968 -0.0674 0.9637 0.0796
-9.000 -0.2403 0.07476 0.07133 -0.0818 0.9484 0.0812
-8.750 -0.2139 0.07153 0.06816 -0.0810 0.9464 0.0822
-8.500 -0.1849 0.06892 0.06556 -0.0820 0.9443 0.0836
-8.250 -0.1717 0.06645 0.06307 -0.0824 0.9359 0.0855
-8.000 -0.1754 0.06060 0.05666 -0.0926 0.9226 0.0934
-7.750 -0.1557 0.05504 0.05119 -0.0942 0.9184 0.0947
-7.500 -0.1244 0.05202 0.04819 -0.0963 0.9159 0.0960
-7.250 -0.0896 0.04896 0.04508 -0.0997 0.9137 0.0981
-7.000 -0.1120 0.03584 0.03091 -0.0983 0.9003 0.0720
-6.750 -0.1201 0.02754 0.02135 -0.0933 0.8900 0.0612
-6.500 -0.0874 0.02517 0.01862 -0.0944 0.8853 0.0615
-6.250 -0.0485 0.02278 0.01581 -0.0964 0.8820 0.0612
-6.000 -0.0268 0.02151 0.01434 -0.0948 0.8717 0.0616
-5.750 0.0147 0.02001 0.01265 -0.0972 0.8666 0.0625
-5.500 0.0408 0.01910 0.01160 -0.0964 0.8559 0.0635
-5.250 0.0832 0.01800 0.01033 -0.0989 0.8489 0.0655
-5.000 0.1083 0.01739 0.00959 -0.0978 0.8359 0.0678
-4.750 0.1368 0.01668 0.00875 -0.0974 0.8233 0.0702
-4.500 0.1667 0.01590 0.00797 -0.0975 0.8112 0.0732
-4.250 0.1968 0.01536 0.00736 -0.0975 0.7988 0.0774
-4.000 0.2193 0.01482 0.00677 -0.0960 0.7834 0.0830
-3.750 0.2422 0.01444 0.00635 -0.0945 0.7675 0.0932
-3.500 0.2639 0.01398 0.00600 -0.0930 0.7512 0.1176
-3.250 0.2869 0.01373 0.00575 -0.0917 0.7344 0.1434
-3.000 0.3102 0.01355 0.00552 -0.0905 0.7174 0.1611
-2.750 0.3334 0.01339 0.00531 -0.0894 0.7006 0.1782
-2.500 0.3563 0.01324 0.00512 -0.0882 0.6844 0.1982
-2.250 0.3790 0.01311 0.00497 -0.0870 0.6690 0.2238
-2.000 0.4005 0.01295 0.00487 -0.0856 0.6547 0.2587
-1.750 0.5297 0.01129 0.00519 -0.1065 0.6356 0.9388
-1.500 0.6179 0.01187 0.00542 -0.1185 0.6186 0.9928
-1.250 0.6636 0.01196 0.00530 -0.1225 0.6050 1.0000
-1.000 0.6833 0.01210 0.00532 -0.1209 0.5937 1.0000
-0.750 0.7042 0.01228 0.00532 -0.1196 0.5835 1.0000
-0.500 0.7241 0.01243 0.00537 -0.1181 0.5733 1.0000
-0.250 0.7446 0.01261 0.00543 -0.1167 0.5638 1.0000
0.000 0.7654 0.01279 0.00548 -0.1154 0.5546 1.0000
0.250 0.7853 0.01297 0.00559 -0.1139 0.5452 1.0000
0.500 0.8069 0.01318 0.00566 -0.1128 0.5366 1.0000
0.750 0.8259 0.01335 0.00580 -0.1111 0.5272 1.0000
1.250 0.8666 0.01376 0.00607 -0.1083 0.5101 1.0000
1.500 0.8892 0.01402 0.00619 -0.1074 0.5025 1.0000
1.750 0.9073 0.01420 0.00638 -0.1055 0.4936 1.0000
2.000 0.9294 0.01446 0.00651 -0.1045 0.4861 1.0000
2.250 0.9476 0.01465 0.00674 -0.1027 0.4776 1.0000
2.500 0.9691 0.01489 0.00688 -0.1016 0.4704 1.0000
2.750 0.9884 0.01513 0.00713 -0.1001 0.4628 1.0000
3.000 1.0088 0.01536 0.00731 -0.0987 0.4558 1.0000
3.250 1.0293 0.01563 0.00755 -0.0975 0.4489 1.0000
3.500 1.0486 0.01586 0.00777 -0.0959 0.4417 1.0000
3.750 1.0716 0.01616 0.00798 -0.0952 0.4358 1.0000
4.000 1.0892 0.01640 0.00829 -0.0934 0.4290 1.0000
4.250 1.1099 0.01666 0.00851 -0.0922 0.4231 1.0000
4.500 1.1308 0.01698 0.00880 -0.0911 0.4172 1.0000
4.750 1.1495 0.01724 0.00912 -0.0895 0.4111 1.0000
5.000 1.1715 0.01754 0.00936 -0.0887 0.4059 1.0000
5.250 1.1912 0.01788 0.00973 -0.0874 0.4005 1.0000
5.500 1.2098 0.01817 0.01007 -0.0859 0.3948 1.0000
5.750 1.2320 0.01849 0.01035 -0.0851 0.3900 1.0000
6.000 1.2517 0.01887 0.01077 -0.0839 0.3850 1.0000
6.250 1.2694 0.01920 0.01116 -0.0823 0.3797 1.0000
6.500 1.2909 0.01954 0.01149 -0.0814 0.3750 1.0000
6.750 1.3130 0.01998 0.01193 -0.0808 0.3705 1.0000
7.000 1.3259 0.02027 0.01233 -0.0783 0.3645 1.0000
7.250 1.3447 0.02055 0.01257 -0.0769 0.3587 1.0000
7.500 1.3593 0.02092 0.01300 -0.0748 0.3527 1.0000
7.750 1.3705 0.02118 0.01331 -0.0720 0.3460 1.0000
8.000 1.3891 0.02154 0.01360 -0.0708 0.3397 1.0000
8.250 1.3939 0.02184 0.01405 -0.0668 0.3340 1.0000
8.500 1.4065 0.02216 0.01441 -0.0644 0.3287 1.0000
8.750 1.4230 0.02259 0.01482 -0.0628 0.3234 1.0000
9.000 1.4261 0.02292 0.01529 -0.0588 0.3175 1.0000
9.250 1.4367 0.02326 0.01561 -0.0562 0.3111 1.0000
9.500 1.4434 0.02372 0.01617 -0.0531 0.3049 1.0000
9.750 1.4501 0.02417 0.01672 -0.0501 0.2988 1.0000
10.000 1.4628 0.02467 0.01719 -0.0483 0.2929 1.0000
10.250 1.4642 0.02528 0.01798 -0.0448 0.2860 1.0000
10.500 1.4706 0.02588 0.01855 -0.0422 0.2787 1.0000
10.750 1.4730 0.02668 0.01954 -0.0393 0.2713 1.0000
11.000 1.4766 0.02753 0.02038 -0.0368 0.2633 1.0000
11.250 1.4783 0.02857 0.02159 -0.0343 0.2538 1.0000
11.500 1.4803 0.02974 0.02281 -0.0320 0.2445 1.0000
11.750 1.4809 0.03112 0.02424 -0.0299 0.2344 1.0000
12.000 1.4793 0.03278 0.02597 -0.0278 0.2209 1.0000
12.250 1.4765 0.03472 0.02795 -0.0260 0.2065 1.0000
12.500 1.4672 0.03732 0.03052 -0.0240 0.1865 1.0000
12.750 1.4540 0.04051 0.03365 -0.0223 0.1664 1.0000
13.000 1.4364 0.04440 0.03746 -0.0209 0.1452 1.0000
13.250 1.4152 0.04903 0.04201 -0.0199 0.1247 1.0000
13.500 1.3925 0.05414 0.04706 -0.0195 0.1037 1.0000
13.750 1.3681 0.05976 0.05263 -0.0195 0.0855 1.0000
14.000 1.3425 0.06580 0.05863 -0.0198 0.0684 1.0000
14.250 1.3195 0.07169 0.06450 -0.0204 0.0553 1.0000
14.500 1.2974 0.07768 0.07049 -0.0212 0.0470 1.0000
14.750 1.2799 0.08320 0.07607 -0.0221 0.0427 1.0000
15.000 1.2632 0.08877 0.08170 -0.0232 0.0395 1.0000
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