GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 655 AIRFOIL (goe655-il) Reynolds number: 200,000 Max Cl/Cd: 64.55 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe655-il-200000.txt Download as CSV file: xf-goe655-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 655 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3437 0.09738 0.09410 -0.0415 1.0000 0.0769
-9.250 -0.3817 0.09431 0.09115 -0.0424 1.0000 0.0773
-9.000 -0.3899 0.09078 0.08769 -0.0397 1.0000 0.0779
-8.750 -0.3794 0.08960 0.08653 -0.0354 1.0000 0.0788
-8.250 -0.3417 0.08518 0.08212 -0.0373 0.9949 0.0837
-8.000 -0.3669 0.06855 0.06538 -0.0670 0.9748 0.0905
-7.750 -0.3302 0.06983 0.06675 -0.0618 0.9737 0.0921
-7.500 -0.3760 0.04174 0.03721 -0.0837 0.9528 0.0654
-7.250 -0.3579 0.03693 0.03208 -0.0852 0.9443 0.0634
-7.000 -0.3286 0.03256 0.02715 -0.0879 0.9404 0.0631
-6.750 -0.3091 0.02979 0.02396 -0.0875 0.9303 0.0631
-6.500 -0.2742 0.02705 0.02078 -0.0895 0.9265 0.0633
-6.250 -0.2332 0.02508 0.01841 -0.0923 0.9241 0.0648
-6.000 -0.2076 0.02395 0.01697 -0.0916 0.9136 0.0661
-5.750 -0.1669 0.02188 0.01463 -0.0939 0.9093 0.0672
-5.500 -0.1372 0.02036 0.01305 -0.0940 0.8993 0.0688
-5.250 -0.0995 0.01926 0.01190 -0.0956 0.8929 0.0716
-5.000 -0.0719 0.01848 0.01103 -0.0952 0.8826 0.0741
-4.750 -0.0372 0.01761 0.01003 -0.0960 0.8759 0.0764
-4.500 -0.0120 0.01671 0.00910 -0.0951 0.8649 0.0788
-4.250 0.0192 0.01591 0.00833 -0.0955 0.8571 0.0832
-4.000 0.0448 0.01541 0.00777 -0.0947 0.8453 0.0878
-3.750 0.0701 0.01472 0.00711 -0.0939 0.8341 0.0935
-3.500 0.0990 0.01422 0.00655 -0.0937 0.8243 0.1020
-3.250 0.1230 0.01371 0.00609 -0.0926 0.8120 0.1173
-3.000 0.1468 0.01306 0.00568 -0.0917 0.8002 0.1617
-2.750 0.1715 0.01249 0.00545 -0.0910 0.7889 0.2528
-2.500 0.1977 0.01225 0.00528 -0.0904 0.7770 0.3067
-2.250 0.2223 0.01209 0.00518 -0.0894 0.7636 0.3487
-2.000 0.2472 0.01192 0.00508 -0.0886 0.7505 0.3900
-1.500 0.2972 0.01160 0.00489 -0.0868 0.7251 0.4831
-1.250 0.3195 0.01137 0.00484 -0.0854 0.7113 0.5424
-1.000 0.3390 0.01102 0.00485 -0.0833 0.6975 0.6372
-0.750 0.3602 0.01061 0.00493 -0.0809 0.6838 0.7905
-0.500 0.4300 0.01055 0.00494 -0.0884 0.6657 0.9301
-0.250 0.4896 0.01066 0.00486 -0.0944 0.6462 0.9750
0.000 0.5503 0.01076 0.00470 -0.1011 0.6254 1.0000
0.250 0.5689 0.01085 0.00464 -0.0992 0.6073 1.0000
0.500 0.5879 0.01097 0.00460 -0.0974 0.5887 1.0000
0.750 0.6073 0.01112 0.00459 -0.0957 0.5700 1.0000
1.000 0.6270 0.01132 0.00461 -0.0940 0.5519 1.0000
1.250 0.6471 0.01154 0.00466 -0.0924 0.5347 1.0000
1.500 0.6674 0.01177 0.00473 -0.0909 0.5182 1.0000
1.750 0.6878 0.01202 0.00482 -0.0893 0.5026 1.0000
2.000 0.7087 0.01228 0.00493 -0.0879 0.4887 1.0000
2.500 0.7520 0.01279 0.00521 -0.0854 0.4657 1.0000
2.750 0.7744 0.01307 0.00538 -0.0843 0.4565 1.0000
3.000 0.7966 0.01333 0.00555 -0.0832 0.4473 1.0000
3.250 0.8193 0.01360 0.00574 -0.0821 0.4391 1.0000
3.500 0.8418 0.01385 0.00593 -0.0811 0.4310 1.0000
3.750 0.8649 0.01414 0.00614 -0.0801 0.4239 1.0000
4.000 0.8877 0.01439 0.00636 -0.0791 0.4167 1.0000
4.250 0.9118 0.01473 0.00658 -0.0785 0.4106 1.0000
4.500 0.9343 0.01496 0.00685 -0.0774 0.4042 1.0000
4.750 0.9578 0.01524 0.00708 -0.0766 0.3985 1.0000
5.000 0.9821 0.01559 0.00736 -0.0760 0.3931 1.0000
5.250 1.0045 0.01584 0.00766 -0.0750 0.3872 1.0000
5.500 1.0278 0.01613 0.00790 -0.0742 0.3815 1.0000
5.750 1.0515 0.01648 0.00822 -0.0735 0.3761 1.0000
6.000 1.0735 0.01674 0.00854 -0.0724 0.3703 1.0000
6.250 1.0967 0.01705 0.00882 -0.0717 0.3650 1.0000
6.500 1.1201 0.01743 0.00918 -0.0709 0.3597 1.0000
6.750 1.1411 0.01770 0.00953 -0.0698 0.3538 1.0000
7.000 1.1638 0.01803 0.00983 -0.0689 0.3481 1.0000
7.250 1.1852 0.01839 0.01022 -0.0679 0.3422 1.0000
7.500 1.2048 0.01867 0.01056 -0.0665 0.3355 1.0000
7.750 1.2277 0.01909 0.01089 -0.0657 0.3291 1.0000
8.000 1.2437 0.01934 0.01128 -0.0637 0.3217 1.0000
8.250 1.2636 0.01970 0.01159 -0.0625 0.3148 1.0000
8.500 1.2793 0.02004 0.01204 -0.0604 0.3070 1.0000
8.750 1.2964 0.02039 0.01237 -0.0587 0.2994 1.0000
9.000 1.3103 0.02079 0.01286 -0.0564 0.2910 1.0000
9.250 1.3247 0.02118 0.01322 -0.0543 0.2834 1.0000
9.500 1.3352 0.02162 0.01375 -0.0514 0.2751 1.0000
9.750 1.3482 0.02208 0.01417 -0.0491 0.2680 1.0000
10.000 1.3591 0.02261 0.01478 -0.0466 0.2603 1.0000
10.250 1.3706 0.02309 0.01526 -0.0442 0.2536 1.0000
10.500 1.3818 0.02368 0.01590 -0.0419 0.2469 1.0000
10.750 1.3920 0.02424 0.01650 -0.0396 0.2404 1.0000
11.000 1.4033 0.02491 0.01715 -0.0376 0.2345 1.0000
11.250 1.4135 0.02559 0.01793 -0.0355 0.2285 1.0000
11.500 1.4246 0.02632 0.01865 -0.0336 0.2236 1.0000
11.750 1.4360 0.02714 0.01954 -0.0319 0.2188 1.0000
12.000 1.4456 0.02798 0.02047 -0.0301 0.2139 1.0000
12.250 1.4559 0.02886 0.02134 -0.0284 0.2095 1.0000
12.500 1.4653 0.02986 0.02241 -0.0268 0.2050 1.0000
12.750 1.4731 0.03091 0.02358 -0.0252 0.2005 1.0000
13.000 1.4820 0.03198 0.02467 -0.0237 0.1965 1.0000
13.250 1.4915 0.03314 0.02583 -0.0224 0.1924 1.0000
13.500 1.4961 0.03450 0.02735 -0.0209 0.1881 1.0000
13.750 1.5028 0.03583 0.02876 -0.0196 0.1845 1.0000
14.000 1.5126 0.03707 0.02992 -0.0186 0.1799 1.0000
14.250 1.5129 0.03888 0.03196 -0.0173 0.1762 1.0000
14.500 1.5148 0.04069 0.03390 -0.0163 0.1720 1.0000
14.750 1.5177 0.04247 0.03567 -0.0154 0.1674 1.0000
15.000 1.5184 0.04456 0.03788 -0.0146 0.1634 1.0000
15.250 1.5140 0.04718 0.04069 -0.0141 0.1584 1.0000
15.500 1.5114 0.04972 0.04324 -0.0137 0.1534 1.0000
15.750 1.5058 0.05280 0.04650 -0.0136 0.1484 1.0000
16.000 1.4965 0.05650 0.05035 -0.0141 0.1419 1.0000
16.250 1.4876 0.06034 0.05429 -0.0146 0.1357 1.0000
16.500 1.4755 0.06491 0.05902 -0.0158 0.1275 1.0000
16.750 1.4631 0.06978 0.06403 -0.0172 0.1178 1.0000
17.000 1.4478 0.07517 0.06952 -0.0188 0.1063 1.0000
17.250 1.4281 0.08130 0.07568 -0.0208 0.0932 1.0000
17.500 1.4000 0.08884 0.08319 -0.0235 0.0776 1.0000
17.750 1.3743 0.09620 0.09055 -0.0262 0.0671 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 655 AIRFOIL (goe655-il)