GOE 298 AIRFOIL (goe298-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 298 AIRFOIL (goe298-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.36 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe298-il-1000000-n5.txt Download as CSV file: xf-goe298-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 298 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
------ -------- --------- --------- -------- -------- --------
-15.250 -1.2241 0.03243 0.02898 -0.0888 1.0000 0.0330
-15.000 -1.2150 0.02881 0.02513 -0.0902 1.0000 0.0332
-14.750 -1.1979 0.02684 0.02302 -0.0907 1.0000 0.0335
-14.500 -1.1780 0.02535 0.02141 -0.0909 1.0000 0.0337
-14.250 -1.1575 0.02391 0.01987 -0.0910 1.0000 0.0340
-14.000 -1.1322 0.02261 0.01847 -0.0919 0.9732 0.0344
-13.750 -1.1059 0.02158 0.01730 -0.0925 0.9352 0.0348
-13.500 -1.0834 0.02076 0.01636 -0.0921 0.9184 0.0352
-13.250 -1.0596 0.02002 0.01550 -0.0918 0.9074 0.0356
-13.000 -1.0351 0.01934 0.01472 -0.0915 0.8981 0.0360
-12.750 -1.0100 0.01873 0.01401 -0.0913 0.8889 0.0365
-12.500 -0.9843 0.01816 0.01335 -0.0911 0.8815 0.0370
-12.250 -0.9580 0.01764 0.01274 -0.0909 0.8741 0.0374
-12.000 -0.9317 0.01714 0.01214 -0.0907 0.8675 0.0378
-11.750 -0.9052 0.01653 0.01148 -0.0907 0.8605 0.0384
-11.500 -0.8786 0.01603 0.01090 -0.0905 0.8517 0.0390
-11.250 -0.8515 0.01557 0.01038 -0.0904 0.8417 0.0395
-11.000 -0.8242 0.01516 0.00989 -0.0902 0.8313 0.0402
-10.750 -0.7966 0.01478 0.00943 -0.0901 0.8200 0.0408
-10.500 -0.7689 0.01443 0.00900 -0.0900 0.8059 0.0414
-10.250 -0.7411 0.01413 0.00858 -0.0898 0.7887 0.0419
-10.000 -0.7133 0.01378 0.00814 -0.0897 0.7737 0.0426
-9.750 -0.6853 0.01344 0.00773 -0.0896 0.7613 0.0434
-9.500 -0.6569 0.01315 0.00737 -0.0896 0.7515 0.0442
-9.250 -0.6284 0.01288 0.00704 -0.0895 0.7421 0.0451
-9.000 -0.5997 0.01264 0.00673 -0.0895 0.7342 0.0460
-8.750 -0.5708 0.01241 0.00643 -0.0895 0.7266 0.0467
-8.250 -0.5131 0.01188 0.00583 -0.0894 0.7130 0.0488
-8.000 -0.4841 0.01166 0.00557 -0.0895 0.7068 0.0498
-7.750 -0.4549 0.01147 0.00532 -0.0894 0.7007 0.0508
-7.500 -0.4256 0.01129 0.00509 -0.0894 0.6954 0.0516
-7.250 -0.3964 0.01105 0.00484 -0.0895 0.6896 0.0528
-7.000 -0.3672 0.01087 0.00462 -0.0895 0.6807 0.0540
-6.750 -0.3378 0.01071 0.00442 -0.0895 0.6715 0.0553
-6.500 -0.3084 0.01057 0.00423 -0.0895 0.6614 0.0565
-6.250 -0.2790 0.01041 0.00403 -0.0895 0.6529 0.0578
-6.000 -0.2496 0.01027 0.00386 -0.0896 0.6414 0.0592
-5.750 -0.2200 0.01015 0.00370 -0.0896 0.6302 0.0606
-5.500 -0.1906 0.01005 0.00354 -0.0896 0.6180 0.0620
-5.250 -0.1611 0.00995 0.00338 -0.0896 0.6030 0.0634
-4.750 -0.1023 0.00986 0.00316 -0.0897 0.5667 0.0669
-4.500 -0.0727 0.00980 0.00305 -0.0897 0.5558 0.0684
-4.250 -0.0431 0.00974 0.00296 -0.0898 0.5475 0.0702
-4.000 -0.0134 0.00968 0.00289 -0.0898 0.5415 0.0720
-3.750 0.0163 0.00963 0.00282 -0.0899 0.5361 0.0737
-3.500 0.0460 0.00958 0.00274 -0.0899 0.5305 0.0752
-3.250 0.0756 0.00955 0.00269 -0.0900 0.5247 0.0768
-3.000 0.1054 0.00950 0.00264 -0.0900 0.5201 0.0784
-2.750 0.1351 0.00947 0.00261 -0.0901 0.5153 0.0800
-2.500 0.1649 0.00945 0.00256 -0.0901 0.5108 0.0816
-2.000 0.2243 0.00937 0.00246 -0.0903 0.5021 0.0841
-1.750 0.2541 0.00933 0.00244 -0.0903 0.4987 0.0855
-1.500 0.2839 0.00931 0.00243 -0.0904 0.4945 0.0870
-1.250 0.3135 0.00931 0.00240 -0.0904 0.4892 0.0883
-1.000 0.3432 0.00930 0.00238 -0.0905 0.4841 0.0895
-0.750 0.3730 0.00928 0.00236 -0.0906 0.4799 0.0905
-0.500 0.4027 0.00925 0.00233 -0.0906 0.4743 0.0916
-0.250 0.4322 0.00924 0.00230 -0.0907 0.4669 0.0930
0.000 0.4618 0.00922 0.00229 -0.0908 0.4581 0.0943
0.250 0.4911 0.00927 0.00229 -0.0908 0.4413 0.0957
0.500 0.5178 0.00977 0.00241 -0.0907 0.3539 0.0968
0.750 0.5459 0.01004 0.00253 -0.0906 0.3236 0.0980
1.000 0.5746 0.01018 0.00261 -0.0906 0.3104 0.0991
1.250 0.6036 0.01027 0.00266 -0.0906 0.3010 0.0999
1.500 0.6326 0.01034 0.00271 -0.0906 0.2939 0.1007
1.750 0.6616 0.01041 0.00276 -0.0906 0.2873 0.1027
2.000 0.6907 0.01044 0.00281 -0.0907 0.2827 0.1040
2.250 0.7197 0.01051 0.00287 -0.0907 0.2763 0.1053
2.500 0.7483 0.01063 0.00295 -0.0906 0.2684 0.1067
2.750 0.7773 0.01069 0.00302 -0.0907 0.2639 0.1082
3.000 0.8062 0.01075 0.00309 -0.0907 0.2600 0.1096
3.250 0.8350 0.01084 0.00317 -0.0906 0.2554 0.1106
3.500 0.8635 0.01094 0.00326 -0.0906 0.2503 0.1123
3.750 0.8923 0.01102 0.00335 -0.0906 0.2466 0.1149
4.000 0.9209 0.01109 0.00344 -0.0906 0.2424 0.1176
4.250 0.9493 0.01121 0.00355 -0.0905 0.2363 0.1209
4.750 1.0057 0.01144 0.00380 -0.0904 0.2241 0.1332
5.000 1.0336 0.01158 0.00395 -0.0904 0.2164 0.1531
5.250 1.0617 0.01164 0.00413 -0.0904 0.2095 0.2109
5.500 1.0893 0.01169 0.00437 -0.0905 0.1991 0.3354
5.750 1.1115 0.01079 0.00475 -0.0896 0.1870 0.9149
6.000 1.1349 0.01098 0.00493 -0.0886 0.1726 1.0000
6.250 1.1607 0.01137 0.00520 -0.0882 0.1580 1.0000
6.500 1.1864 0.01175 0.00550 -0.0879 0.1452 1.0000
6.750 1.2122 0.01211 0.00578 -0.0875 0.1353 1.0000
7.000 1.2378 0.01246 0.00607 -0.0871 0.1277 1.0000
7.250 1.2633 0.01281 0.00636 -0.0867 0.1215 1.0000
7.500 1.2891 0.01311 0.00664 -0.0864 0.1175 1.0000
7.750 1.3149 0.01339 0.00691 -0.0860 0.1146 1.0000
8.000 1.3401 0.01371 0.00720 -0.0856 0.1114 1.0000
8.250 1.3648 0.01405 0.00752 -0.0851 0.1081 1.0000
8.500 1.3901 0.01433 0.00780 -0.0846 0.1065 1.0000
8.750 1.4150 0.01462 0.00810 -0.0841 0.1049 1.0000
9.000 1.4394 0.01494 0.00841 -0.0836 0.1031 1.0000
9.250 1.4630 0.01530 0.00876 -0.0830 0.1010 1.0000
9.500 1.4862 0.01567 0.00912 -0.0822 0.0989 1.0000
9.750 1.5091 0.01604 0.00950 -0.0815 0.0972 1.0000
10.000 1.5323 0.01636 0.00984 -0.0808 0.0962 1.0000
10.250 1.5548 0.01671 0.01020 -0.0800 0.0948 1.0000
10.500 1.5763 0.01710 0.01060 -0.0791 0.0931 1.0000
10.750 1.5966 0.01752 0.01103 -0.0780 0.0912 1.0000
11.000 1.6153 0.01799 0.01150 -0.0767 0.0893 1.0000
11.250 1.6321 0.01847 0.01199 -0.0750 0.0876 1.0000
11.500 1.6487 0.01893 0.01248 -0.0733 0.0860 1.0000
11.750 1.6648 0.01947 0.01305 -0.0717 0.0842 1.0000
12.000 1.6799 0.02011 0.01370 -0.0701 0.0820 1.0000
12.250 1.6939 0.02087 0.01446 -0.0686 0.0797 1.0000
12.500 1.7092 0.02159 0.01522 -0.0673 0.0778 1.0000
12.750 1.7232 0.02244 0.01608 -0.0660 0.0744 1.0000
13.000 1.7350 0.02349 0.01712 -0.0646 0.0703 1.0000
13.250 1.7438 0.02479 0.01839 -0.0631 0.0629 1.0000
13.500 1.7350 0.02757 0.02103 -0.0605 0.0425 1.0000
13.750 1.7328 0.02999 0.02343 -0.0587 0.0351 1.0000
14.000 1.7377 0.03187 0.02535 -0.0576 0.0328 1.0000
14.250 1.7439 0.03370 0.02723 -0.0566 0.0314 1.0000
14.500 1.7492 0.03567 0.02924 -0.0557 0.0304 1.0000
14.750 1.7536 0.03773 0.03136 -0.0549 0.0295 1.0000
15.000 1.7593 0.03971 0.03339 -0.0542 0.0290 1.0000
15.250 1.7638 0.04183 0.03558 -0.0535 0.0284 1.0000
15.500 1.7667 0.04415 0.03796 -0.0529 0.0279 1.0000
15.750 1.7680 0.04665 0.04053 -0.0524 0.0275 1.0000
16.000 1.7684 0.04935 0.04329 -0.0519 0.0270 1.0000
16.250 1.7679 0.05224 0.04626 -0.0517 0.0266 1.0000
16.500 1.7665 0.05531 0.04940 -0.0515 0.0262 1.0000
16.750 1.7638 0.05861 0.05277 -0.0515 0.0259 1.0000
17.000 1.7631 0.06174 0.05599 -0.0516 0.0257 1.0000
17.250 1.7615 0.06503 0.05936 -0.0518 0.0255 1.0000
17.500 1.7587 0.06849 0.06291 -0.0521 0.0253 1.0000
17.750 1.7543 0.07224 0.06675 -0.0526 0.0251 1.0000
18.000 1.7485 0.07623 0.07083 -0.0531 0.0248 1.0000
18.250 1.7418 0.08037 0.07506 -0.0538 0.0246 1.0000
18.500 1.7338 0.08469 0.07948 -0.0546 0.0244 1.0000
18.750 1.7238 0.08941 0.08429 -0.0556 0.0242 1.0000
19.000 1.7123 0.09445 0.08944 -0.0568 0.0240 1.0000
19.250 1.6991 0.09980 0.09490 -0.0583 0.0238 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 298 AIRFOIL (goe298-il)