GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il) Reynolds number: 1,000,000 Max Cl/Cd: 119.15 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe335-il-1000000-n5.txt Download as CSV file: xf-goe335-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3371 0.10745 0.10584 -0.0213 1.0000 0.0034
-9.250 -0.3344 0.10419 0.10260 -0.0218 1.0000 0.0034
-9.000 -0.3334 0.10063 0.09906 -0.0224 1.0000 0.0033
-8.750 -0.3278 0.09807 0.09652 -0.0232 0.9998 0.0034
-8.500 -0.3155 0.09282 0.09127 -0.0279 0.9972 0.0032
-8.250 -0.3019 0.09023 0.08869 -0.0304 0.9900 0.0038
-8.000 -0.2905 0.08639 0.08485 -0.0338 0.9819 0.0037
-7.750 -0.2759 0.08213 0.08059 -0.0386 0.9722 0.0040
-7.500 -0.2452 0.07612 0.07455 -0.0490 0.9567 0.0042
-6.500 -0.2028 0.01409 0.00984 -0.1008 0.8018 0.0052
-6.250 -0.1785 0.01282 0.00832 -0.1005 0.7918 0.0056
-6.000 -0.1533 0.01198 0.00726 -0.1001 0.7822 0.0059
-5.750 -0.1276 0.01129 0.00638 -0.0998 0.7728 0.0064
-5.500 -0.1015 0.01070 0.00562 -0.0995 0.7647 0.0068
-5.250 -0.0753 0.01021 0.00496 -0.0991 0.7557 0.0073
-5.000 -0.0489 0.00972 0.00438 -0.0988 0.7469 0.0087
-4.750 -0.0225 0.00935 0.00388 -0.0985 0.7374 0.0099
-4.250 0.0315 0.00905 0.00350 -0.0980 0.7169 0.0143
-4.000 0.0585 0.00895 0.00333 -0.0977 0.7057 0.0160
-3.750 0.0861 0.00919 0.00359 -0.0975 0.6918 0.0177
-3.500 0.1134 0.00938 0.00375 -0.0973 0.6778 0.0196
-3.250 0.1405 0.00938 0.00367 -0.0970 0.6651 0.0214
-3.000 0.1676 0.00944 0.00367 -0.0968 0.6527 0.0232
-2.750 0.1947 0.00950 0.00365 -0.0965 0.6397 0.0243
-2.500 0.2219 0.00962 0.00370 -0.0963 0.6259 0.0250
-2.250 0.2489 0.00970 0.00371 -0.0961 0.6106 0.0254
-2.000 0.2750 0.00930 0.00317 -0.0957 0.5921 0.0264
-1.750 0.3007 0.00889 0.00260 -0.0953 0.5698 0.0274
-1.500 0.3264 0.00874 0.00230 -0.0948 0.5399 0.0279
-1.250 0.3519 0.00870 0.00208 -0.0943 0.5021 0.0281
-1.000 0.3772 0.00871 0.00190 -0.0938 0.4654 0.0282
-0.750 0.4031 0.00871 0.00177 -0.0934 0.4395 0.0286
-0.500 0.4294 0.00869 0.00165 -0.0930 0.4219 0.0289
-0.250 0.4559 0.00866 0.00153 -0.0927 0.4085 0.0287
0.000 0.4827 0.00864 0.00144 -0.0925 0.3974 0.0286
0.250 0.5095 0.00862 0.00138 -0.0922 0.3881 0.0285
0.500 0.5362 0.00863 0.00132 -0.0920 0.3789 0.0285
0.750 0.5630 0.00864 0.00128 -0.0917 0.3690 0.0286
1.000 0.5898 0.00867 0.00126 -0.0915 0.3596 0.0290
1.500 0.6436 0.00872 0.00125 -0.0910 0.3461 0.0321
1.750 0.6705 0.00875 0.00129 -0.0908 0.3412 0.0374
2.000 0.6972 0.00874 0.00136 -0.0906 0.3364 0.0792
2.250 0.7240 0.00871 0.00143 -0.0904 0.3327 0.1202
2.500 0.7501 0.00853 0.00157 -0.0903 0.3280 0.2788
3.000 0.8079 0.00734 0.00188 -0.0913 0.3114 1.0000
3.250 0.8341 0.00746 0.00197 -0.0910 0.3056 1.0000
3.500 0.8606 0.00756 0.00206 -0.0907 0.3015 1.0000
3.750 0.8868 0.00769 0.00217 -0.0904 0.2961 1.0000
4.000 0.9130 0.00781 0.00228 -0.0901 0.2913 1.0000
4.250 0.9394 0.00792 0.00240 -0.0898 0.2868 1.0000
4.500 0.9651 0.00810 0.00254 -0.0895 0.2762 1.0000
4.750 0.9902 0.00832 0.00268 -0.0891 0.2572 1.0000
5.000 1.0137 0.00871 0.00290 -0.0884 0.2233 1.0000
5.250 1.0336 0.00948 0.00334 -0.0872 0.1635 1.0000
5.500 1.0517 0.01047 0.00395 -0.0857 0.0908 1.0000
5.750 1.0737 0.01104 0.00439 -0.0848 0.0617 1.0000
6.000 1.0936 0.01186 0.00497 -0.0836 0.0165 1.0000
6.250 1.1180 0.01216 0.00529 -0.0831 0.0122 1.0000
6.500 1.1415 0.01254 0.00570 -0.0824 0.0093 1.0000
6.750 1.1654 0.01287 0.00607 -0.0818 0.0080 1.0000
7.000 1.1890 0.01322 0.00644 -0.0811 0.0069 1.0000
7.250 1.2116 0.01366 0.00690 -0.0804 0.0059 1.0000
7.500 1.2341 0.01410 0.00739 -0.0795 0.0054 1.0000
7.750 1.2567 0.01452 0.00787 -0.0788 0.0050 1.0000
8.000 1.2788 0.01495 0.00834 -0.0779 0.0045 1.0000
8.250 1.3005 0.01541 0.00883 -0.0771 0.0041 1.0000
8.500 1.3197 0.01610 0.00957 -0.0758 0.0036 1.0000
8.750 1.3402 0.01662 0.01015 -0.0747 0.0035 1.0000
9.000 1.3599 0.01718 0.01078 -0.0736 0.0033 1.0000
9.250 1.3786 0.01780 0.01147 -0.0722 0.0031 1.0000
9.500 1.3964 0.01845 0.01218 -0.0708 0.0029 1.0000
9.750 1.4134 0.01911 0.01294 -0.0693 0.0027 1.0000
10.000 1.4292 0.01982 0.01371 -0.0676 0.0026 1.0000
10.250 1.4437 0.02056 0.01451 -0.0657 0.0025 1.0000
10.500 1.4534 0.02140 0.01543 -0.0630 0.0024 1.0000
10.750 1.4557 0.02256 0.01669 -0.0592 0.0022 1.0000
11.000 1.4571 0.02382 0.01807 -0.0556 0.0022 1.0000
11.250 1.4623 0.02493 0.01928 -0.0528 0.0021 1.0000
11.500 1.4673 0.02612 0.02056 -0.0502 0.0021 1.0000
11.750 1.4713 0.02746 0.02201 -0.0478 0.0020 1.0000
12.000 1.4726 0.02911 0.02377 -0.0454 0.0020 1.0000
12.250 1.4759 0.03074 0.02550 -0.0437 0.0019 1.0000
12.500 1.4747 0.03292 0.02781 -0.0419 0.0018 1.0000
12.750 1.4728 0.03534 0.03036 -0.0405 0.0018 1.0000
13.000 1.4755 0.03743 0.03254 -0.0397 0.0017 1.0000
13.250 1.4712 0.04043 0.03567 -0.0389 0.0017 1.0000
13.500 1.4735 0.04282 0.03818 -0.0385 0.0016 1.0000
13.750 1.4678 0.04630 0.04180 -0.0383 0.0016 1.0000
14.000 1.4607 0.05011 0.04575 -0.0385 0.0016 1.0000
14.250 1.4528 0.05425 0.05003 -0.0390 0.0016 1.0000
14.500 1.4485 0.05809 0.05398 -0.0398 0.0015 1.0000
14.750 1.4446 0.06204 0.05805 -0.0408 0.0015 1.0000
15.000 1.4338 0.06719 0.06335 -0.0423 0.0015 1.0000
15.250 1.4276 0.07190 0.06818 -0.0439 0.0015 1.0000
15.500 1.4207 0.07689 0.07328 -0.0459 0.0015 1.0000
15.750 1.4145 0.08193 0.07843 -0.0480 0.0014 1.0000
16.000 1.4024 0.08806 0.08471 -0.0505 0.0014 1.0000
16.250 1.3929 0.09386 0.09063 -0.0530 0.0014 1.0000
16.500 1.3842 0.09967 0.09655 -0.0557 0.0014 1.0000
16.750 1.3754 0.10560 0.10259 -0.0585 0.0014 1.0000
17.000 1.3625 0.11237 0.10950 -0.0617 0.0014 1.0000
17.250 1.3543 0.11844 0.11567 -0.0648 0.0014 1.0000
17.500 1.3420 0.12543 0.12279 -0.0684 0.0014 1.0000
17.750 1.3302 0.13250 0.12999 -0.0721 0.0014 1.0000
18.000 1.3178 0.13984 0.13745 -0.0762 0.0014 1.0000
18.250 1.3051 0.14746 0.14521 -0.0805 0.0014 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 335 (D.F.W.) AIRFOIL (goe335-il)