Dayton-Wright 6 (daytonwright6-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Dayton-Wright 6 (daytonwright6-il) Reynolds number: 500,000 Max Cl/Cd: 92.63 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-daytonwright6-il-500000.txt Download as CSV file: xf-daytonwright6-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1942 0.08717 0.08489 -0.0683 0.9818 0.0400
-10.500 -0.1824 0.08358 0.08130 -0.0717 0.9760 0.0409
-10.250 -0.2029 0.07090 0.06864 -0.0887 0.9641 0.0445
-10.000 -0.1851 0.06847 0.06621 -0.0906 0.9597 0.0450
-9.750 -0.1709 0.06607 0.06380 -0.0928 0.9518 0.0455
-9.500 -0.1532 0.06308 0.06079 -0.0969 0.9449 0.0462
-9.250 -0.2472 0.02771 0.02349 -0.1165 0.9154 0.0378
-9.000 -0.2353 0.02396 0.01944 -0.1155 0.9060 0.0372
-8.750 -0.2120 0.02212 0.01725 -0.1154 0.8987 0.0374
-8.500 -0.1944 0.02058 0.01545 -0.1139 0.8898 0.0374
-8.250 -0.1702 0.01907 0.01365 -0.1135 0.8824 0.0374
-8.000 -0.1504 0.01811 0.01248 -0.1119 0.8738 0.0375
-7.750 -0.1249 0.01715 0.01131 -0.1115 0.8665 0.0376
-7.500 -0.1034 0.01643 0.01043 -0.1101 0.8582 0.0377
-7.250 -0.0784 0.01549 0.00932 -0.1095 0.8506 0.0379
-7.000 -0.0564 0.01451 0.00821 -0.1083 0.8423 0.0382
-6.750 -0.0317 0.01372 0.00732 -0.1076 0.8340 0.0388
-6.500 -0.0095 0.01321 0.00678 -0.1062 0.8241 0.0395
-6.250 0.0158 0.01281 0.00628 -0.1055 0.8146 0.0402
-6.000 0.0374 0.01243 0.00586 -0.1040 0.8038 0.0407
-5.750 0.0610 0.01208 0.00544 -0.1029 0.7943 0.0414
-5.500 0.0840 0.01176 0.00505 -0.1016 0.7836 0.0419
-5.250 0.1060 0.01147 0.00471 -0.1002 0.7719 0.0427
-5.000 0.1284 0.01121 0.00439 -0.0988 0.7595 0.0433
-4.750 0.1505 0.01100 0.00409 -0.0973 0.7450 0.0441
-4.500 0.1709 0.01069 0.00373 -0.0955 0.7273 0.0453
-4.250 0.1912 0.01050 0.00347 -0.0937 0.7051 0.0468
-4.000 0.2111 0.01040 0.00326 -0.0918 0.6800 0.0491
-3.750 0.2309 0.01037 0.00308 -0.0899 0.6550 0.0515
-3.500 0.2504 0.01031 0.00294 -0.0879 0.6333 0.0569
-3.250 0.2707 0.01024 0.00285 -0.0862 0.6151 0.0720
-3.000 0.2916 0.01019 0.00280 -0.0847 0.5999 0.0964
-2.750 0.3133 0.01019 0.00278 -0.0833 0.5868 0.1140
-2.500 0.3363 0.01019 0.00277 -0.0822 0.5757 0.1269
-2.250 0.3588 0.01019 0.00276 -0.0810 0.5661 0.1433
-2.000 0.3815 0.01018 0.00276 -0.0799 0.5567 0.1600
-1.750 0.4042 0.01016 0.00276 -0.0788 0.5482 0.1797
-1.500 0.4265 0.01014 0.00276 -0.0776 0.5398 0.2060
-1.250 0.4485 0.01008 0.00278 -0.0764 0.5324 0.2412
-1.000 0.4697 0.00996 0.00281 -0.0750 0.5249 0.2980
-0.750 0.5958 0.00874 0.00341 -0.0969 0.5125 0.9462
-0.500 0.6319 0.00909 0.00365 -0.0984 0.5040 0.9737
-0.250 0.6791 0.00933 0.00381 -0.1025 0.4956 0.9847
0.000 0.7293 0.00955 0.00390 -0.1074 0.4869 0.9920
0.250 0.7876 0.00961 0.00390 -0.1142 0.4776 0.9985
0.500 0.8173 0.00972 0.00391 -0.1148 0.4698 1.0000
0.750 0.8373 0.00978 0.00395 -0.1133 0.4620 1.0000
1.000 0.8561 0.00990 0.00400 -0.1116 0.4545 1.0000
1.250 0.8759 0.00998 0.00406 -0.1101 0.4473 1.0000
1.500 0.8950 0.01010 0.00413 -0.1084 0.4397 1.0000
1.750 0.9144 0.01023 0.00421 -0.1068 0.4323 1.0000
2.000 0.9337 0.01035 0.00430 -0.1052 0.4245 1.0000
2.250 0.9526 0.01050 0.00440 -0.1035 0.4170 1.0000
2.500 0.9718 0.01064 0.00450 -0.1019 0.4092 1.0000
2.750 0.9902 0.01082 0.00463 -0.1001 0.4023 1.0000
3.000 1.0096 0.01096 0.00476 -0.0985 0.3951 1.0000
3.250 1.0271 0.01118 0.00491 -0.0966 0.3885 1.0000
3.500 1.0468 0.01131 0.00505 -0.0951 0.3820 1.0000
3.750 1.0646 0.01151 0.00521 -0.0933 0.3758 1.0000
4.000 1.0826 0.01172 0.00540 -0.0915 0.3703 1.0000
4.250 1.1014 0.01189 0.00557 -0.0898 0.3647 1.0000
4.500 1.1180 0.01212 0.00575 -0.0878 0.3591 1.0000
4.750 1.1344 0.01233 0.00596 -0.0857 0.3545 1.0000
5.000 1.1511 0.01249 0.00614 -0.0837 0.3496 1.0000
5.250 1.1662 0.01270 0.00633 -0.0813 0.3448 1.0000
5.500 1.1815 0.01299 0.00658 -0.0791 0.3404 1.0000
5.750 1.1987 0.01312 0.00677 -0.0772 0.3352 1.0000
6.000 1.2141 0.01335 0.00698 -0.0751 0.3295 1.0000
6.250 1.2291 0.01365 0.00724 -0.0729 0.3240 1.0000
6.500 1.2470 0.01382 0.00747 -0.0713 0.3191 1.0000
6.750 1.2633 0.01407 0.00773 -0.0694 0.3143 1.0000
7.000 1.2780 0.01444 0.00806 -0.0674 0.3090 1.0000
7.250 1.2962 0.01461 0.00830 -0.0659 0.3037 1.0000
7.500 1.3123 0.01490 0.00861 -0.0642 0.2985 1.0000
7.750 1.3267 0.01531 0.00898 -0.0622 0.2935 1.0000
8.000 1.3452 0.01552 0.00928 -0.0609 0.2884 1.0000
8.250 1.3611 0.01585 0.00962 -0.0592 0.2827 1.0000
8.500 1.3755 0.01625 0.01003 -0.0574 0.2763 1.0000
8.750 1.3919 0.01659 0.01041 -0.0560 0.2690 1.0000
9.000 1.4052 0.01706 0.01087 -0.0541 0.2613 1.0000
9.250 1.4200 0.01751 0.01133 -0.0525 0.2518 1.0000
9.500 1.4335 0.01803 0.01186 -0.0508 0.2413 1.0000
9.750 1.4442 0.01872 0.01252 -0.0489 0.2275 1.0000
10.000 1.4515 0.01963 0.01335 -0.0465 0.2088 1.0000
10.250 1.4515 0.02100 0.01456 -0.0435 0.1815 1.0000
10.500 1.4431 0.02300 0.01634 -0.0398 0.1489 1.0000
10.750 1.4301 0.02545 0.01858 -0.0360 0.1145 1.0000
11.000 1.4142 0.02830 0.02125 -0.0324 0.0840 1.0000
11.250 1.3929 0.03181 0.02459 -0.0289 0.0527 1.0000
11.500 1.3706 0.03574 0.02842 -0.0262 0.0289 1.0000
11.750 1.3653 0.03847 0.03120 -0.0248 0.0245 1.0000
12.000 1.3623 0.04117 0.03397 -0.0238 0.0225 1.0000
12.250 1.3613 0.04379 0.03668 -0.0232 0.0215 1.0000
12.500 1.3596 0.04659 0.03959 -0.0227 0.0207 1.0000
12.750 1.3570 0.04962 0.04272 -0.0224 0.0201 1.0000
13.000 1.3520 0.05301 0.04621 -0.0223 0.0195 1.0000
13.250 1.3438 0.05689 0.05019 -0.0223 0.0190 1.0000
13.500 1.3356 0.06085 0.05426 -0.0225 0.0187 1.0000
13.750 1.3242 0.06530 0.05883 -0.0228 0.0182 1.0000
14.000 1.3171 0.06927 0.06290 -0.0232 0.0179 1.0000
14.250 1.3089 0.07343 0.06718 -0.0237 0.0179 1.0000
14.500 1.2996 0.07783 0.07169 -0.0243 0.0176 1.0000
14.750 1.2908 0.08224 0.07620 -0.0250 0.0173 1.0000
15.000 1.2811 0.08682 0.08089 -0.0258 0.0171 1.0000
15.250 1.2730 0.09127 0.08543 -0.0267 0.0169 1.0000
15.500 1.2627 0.09610 0.09035 -0.0277 0.0167 1.0000
15.750 1.2538 0.10077 0.09511 -0.0288 0.0165 1.0000
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