GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il) Reynolds number: 100,000 Max Cl/Cd: 56.57 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe335-il-100000.txt Download as CSV file: xf-goe335-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 335 (D.F.W.) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3195 0.09184 0.08727 -0.0231 1.0000 0.0580
-7.000 -0.3217 0.08979 0.08531 -0.0231 1.0000 0.0599
-6.750 -0.3220 0.08811 0.08372 -0.0256 1.0000 0.0621
-6.500 -0.3188 0.08731 0.08297 -0.0318 1.0000 0.0633
-6.250 -0.3101 0.08617 0.08179 -0.0377 1.0000 0.0638
-6.000 -0.3153 0.07984 0.07565 -0.0290 1.0000 0.0655
-5.750 -0.3143 0.07712 0.07298 -0.0261 1.0000 0.0675
-5.500 -0.3142 0.07494 0.07085 -0.0250 1.0000 0.0696
-5.250 -0.3143 0.07292 0.06887 -0.0246 1.0000 0.0720
-5.000 -0.3087 0.07103 0.06696 -0.0267 1.0000 0.0754
-4.750 -0.2877 0.06897 0.06469 -0.0346 1.0000 0.0781
-4.500 -0.2914 0.06534 0.06120 -0.0304 1.0000 0.0794
-4.250 -0.2880 0.06282 0.05872 -0.0283 1.0000 0.0820
-4.000 -0.2758 0.06038 0.05624 -0.0291 1.0000 0.0867
-3.750 -0.2359 0.05623 0.05188 -0.0370 0.9963 0.0940
-3.500 -0.1844 0.05185 0.04728 -0.0453 0.9872 0.1083
-3.250 -0.1356 0.04783 0.04304 -0.0524 0.9784 0.1225
-3.000 -0.0895 0.04411 0.03916 -0.0583 0.9708 0.1378
-2.750 -0.0461 0.04154 0.03627 -0.0635 0.9617 0.1638
-2.500 -0.0058 0.03836 0.03304 -0.0674 0.9557 0.1935
-2.250 0.0263 0.03586 0.03045 -0.0694 0.9460 0.2233
-2.000 0.0611 0.03347 0.02802 -0.0716 0.9380 0.2673
-1.500 0.1834 0.02591 0.01843 -0.0814 0.9247 0.1166
-1.250 0.2292 0.02378 0.01560 -0.0836 0.9169 0.1046
-1.000 0.2705 0.02225 0.01373 -0.0855 0.9078 0.1068
-0.750 0.3196 0.02075 0.01194 -0.0886 0.9012 0.1058
-0.500 0.3571 0.01935 0.01049 -0.0898 0.8903 0.1079
-0.250 0.3960 0.01827 0.00940 -0.0911 0.8796 0.1133
0.000 0.4348 0.01730 0.00848 -0.0924 0.8684 0.1273
0.250 0.4716 0.01637 0.00760 -0.0931 0.8561 0.1456
0.500 0.5226 0.01340 0.00652 -0.0964 0.8444 1.0000
0.750 0.5517 0.01338 0.00623 -0.0957 0.8256 1.0000
1.000 0.5803 0.01339 0.00602 -0.0950 0.8054 1.0000
1.250 0.6072 0.01345 0.00590 -0.0939 0.7839 1.0000
1.500 0.6325 0.01355 0.00583 -0.0926 0.7601 1.0000
1.750 0.6564 0.01367 0.00578 -0.0911 0.7333 1.0000
2.000 0.6803 0.01377 0.00572 -0.0896 0.7052 1.0000
2.250 0.7043 0.01391 0.00568 -0.0882 0.6768 1.0000
2.500 0.7286 0.01412 0.00573 -0.0870 0.6496 1.0000
2.750 0.7532 0.01439 0.00582 -0.0860 0.6254 1.0000
3.000 0.7780 0.01469 0.00596 -0.0852 0.6041 1.0000
3.250 0.8030 0.01504 0.00617 -0.0844 0.5854 1.0000
3.500 0.8280 0.01543 0.00650 -0.0837 0.5688 1.0000
3.750 0.8534 0.01583 0.00683 -0.0832 0.5547 1.0000
4.000 0.8790 0.01625 0.00719 -0.0827 0.5421 1.0000
4.250 0.9046 0.01667 0.00754 -0.0822 0.5300 1.0000
4.500 0.9296 0.01709 0.00798 -0.0816 0.5175 1.0000
4.750 0.9542 0.01753 0.00844 -0.0809 0.5052 1.0000
5.000 0.9791 0.01802 0.00898 -0.0804 0.4945 1.0000
5.250 1.0048 0.01856 0.00953 -0.0800 0.4857 1.0000
5.500 1.0300 0.01910 0.01014 -0.0795 0.4764 1.0000
5.750 1.0543 0.01966 0.01086 -0.0789 0.4665 1.0000
6.000 1.0790 0.02022 0.01147 -0.0784 0.4562 1.0000
6.250 1.1041 0.02076 0.01202 -0.0778 0.4452 1.0000
6.500 1.1260 0.02114 0.01250 -0.0766 0.4290 1.0000
6.750 1.1463 0.02137 0.01283 -0.0751 0.4088 1.0000
7.000 1.1678 0.02160 0.01308 -0.0737 0.3904 1.0000
7.250 1.1875 0.02178 0.01337 -0.0722 0.3710 1.0000
7.500 1.2050 0.02176 0.01349 -0.0701 0.3477 1.0000
7.750 1.2179 0.02153 0.01343 -0.0673 0.3126 1.0000
8.000 1.2243 0.02172 0.01343 -0.0636 0.2072 1.0000
8.250 1.2130 0.02556 0.01598 -0.0589 0.0781 1.0000
8.500 1.2154 0.02789 0.01832 -0.0555 0.0633 1.0000
8.750 1.2228 0.02952 0.02013 -0.0525 0.0566 1.0000
9.000 1.2239 0.03145 0.02211 -0.0492 0.0527 1.0000
9.250 1.2273 0.03305 0.02383 -0.0459 0.0493 1.0000
9.500 1.2319 0.03465 0.02553 -0.0430 0.0461 1.0000
9.750 1.2369 0.03649 0.02738 -0.0404 0.0438 1.0000
10.000 1.2492 0.03881 0.02963 -0.0386 0.0421 1.0000
10.250 1.2862 0.04209 0.03294 -0.0394 0.0408 1.0000
10.500 1.3191 0.04543 0.03653 -0.0398 0.0404 1.0000
10.750 1.3377 0.04852 0.03994 -0.0388 0.0398 1.0000
11.000 1.3461 0.05133 0.04310 -0.0367 0.0390 1.0000
11.250 1.3481 0.05420 0.04632 -0.0342 0.0383 1.0000
11.500 1.3464 0.05740 0.04986 -0.0315 0.0382 1.0000
11.750 1.3412 0.06092 0.05370 -0.0291 0.0386 1.0000
12.000 1.3323 0.06466 0.05774 -0.0268 0.0390 1.0000
12.250 1.3214 0.06862 0.06197 -0.0252 0.0394 1.0000
12.500 1.3075 0.07293 0.06654 -0.0242 0.0398 1.0000
12.750 1.2928 0.07763 0.07146 -0.0239 0.0402 1.0000
13.000 1.2778 0.08281 0.07685 -0.0242 0.0406 1.0000
13.250 1.2715 0.08871 0.08293 -0.0248 0.0414 1.0000
13.500 1.2521 0.09276 0.08721 -0.0262 0.0418 1.0000
13.750 1.2283 0.09812 0.09280 -0.0291 0.0422 1.0000
14.000 1.2010 0.10493 0.09984 -0.0335 0.0425 1.0000
14.250 1.1706 0.11332 0.10845 -0.0396 0.0429 1.0000
14.500 1.1345 0.12420 0.11951 -0.0482 0.0433 1.0000
14.750 1.0650 0.14824 0.14363 -0.0660 0.0490 1.0000
15.000 1.0579 0.15626 0.15163 -0.0698 0.0507 1.0000
15.250 1.0585 0.16197 0.15733 -0.0716 0.0517 1.0000
15.500 0.8552 0.16785 0.16373 -0.0706 0.0635 1.0000
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Polar data table (+)
Polar graphs
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