GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 655 AIRFOIL (goe655-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.99 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe655-il-1000000-n5.txt Download as CSV file: xf-goe655-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0022 0.05271 0.04977 -0.0860 1.0000 0.0127
-16.250 -1.0624 0.03957 0.03635 -0.0965 1.0000 0.0125
-16.000 -1.0891 0.03246 0.02903 -0.1029 1.0000 0.0126
-15.750 -1.1086 0.02945 0.02590 -0.1024 1.0000 0.0126
-15.500 -1.1289 0.02800 0.02435 -0.0977 1.0000 0.0126
-15.250 -1.1145 0.02655 0.02282 -0.0982 0.9977 0.0130
-15.000 -1.0926 0.02520 0.02137 -0.0994 0.9946 0.0134
-14.750 -1.0721 0.02407 0.02015 -0.0998 0.9914 0.0138
-14.500 -1.0493 0.02305 0.01905 -0.1003 0.9881 0.0142
-14.250 -1.0241 0.02209 0.01799 -0.1012 0.9855 0.0146
-14.000 -0.9972 0.02122 0.01708 -0.1021 0.9837 0.0151
-13.750 -0.9750 0.02053 0.01634 -0.1018 0.9799 0.0156
-13.500 -0.9499 0.01986 0.01561 -0.1021 0.9769 0.0161
-13.250 -0.9222 0.01924 0.01494 -0.1027 0.9746 0.0167
-13.000 -0.8924 0.01861 0.01424 -0.1037 0.9729 0.0173
-12.750 -0.8636 0.01801 0.01356 -0.1044 0.9708 0.0177
-12.500 -0.8385 0.01746 0.01299 -0.1044 0.9664 0.0182
-12.250 -0.8090 0.01697 0.01246 -0.1051 0.9632 0.0187
-12.000 -0.7779 0.01652 0.01197 -0.1061 0.9604 0.0192
-11.750 -0.7488 0.01609 0.01149 -0.1066 0.9566 0.0198
-11.500 -0.7220 0.01568 0.01102 -0.1066 0.9511 0.0203
-11.250 -0.6923 0.01529 0.01056 -0.1072 0.9462 0.0208
-11.000 -0.6650 0.01491 0.01011 -0.1072 0.9404 0.0211
-10.750 -0.6399 0.01443 0.00958 -0.1069 0.9330 0.0216
-10.500 -0.6130 0.01406 0.00917 -0.1068 0.9258 0.0221
-10.250 -0.5877 0.01375 0.00881 -0.1063 0.9166 0.0225
-10.000 -0.5616 0.01349 0.00850 -0.1060 0.9076 0.0231
-9.750 -0.5362 0.01322 0.00816 -0.1054 0.8975 0.0236
-9.500 -0.5112 0.01294 0.00781 -0.1048 0.8874 0.0240
-9.250 -0.4863 0.01267 0.00746 -0.1042 0.8765 0.0244
-9.000 -0.4612 0.01245 0.00716 -0.1035 0.8636 0.0248
-8.750 -0.4364 0.01225 0.00686 -0.1028 0.8488 0.0251
-8.500 -0.4139 0.01188 0.00638 -0.1017 0.8287 0.0257
-8.250 -0.3907 0.01165 0.00606 -0.1007 0.8047 0.0263
-8.000 -0.3673 0.01150 0.00579 -0.0996 0.7812 0.0268
-7.750 -0.3433 0.01136 0.00554 -0.0987 0.7609 0.0273
-7.500 -0.3189 0.01121 0.00529 -0.0979 0.7435 0.0278
-7.250 -0.2943 0.01107 0.00505 -0.0971 0.7267 0.0283
-7.000 -0.2696 0.01091 0.00480 -0.0963 0.7116 0.0288
-6.750 -0.2442 0.01075 0.00456 -0.0957 0.6991 0.0291
-6.500 -0.2181 0.01058 0.00433 -0.0952 0.6913 0.0295
-6.250 -0.1923 0.01040 0.00409 -0.0947 0.6828 0.0299
-6.000 -0.1665 0.01017 0.00382 -0.0941 0.6749 0.0307
-5.750 -0.1406 0.01001 0.00362 -0.0936 0.6650 0.0315
-5.500 -0.1143 0.00987 0.00344 -0.0931 0.6551 0.0322
-5.250 -0.0882 0.00975 0.00326 -0.0926 0.6445 0.0329
-5.000 -0.0618 0.00963 0.00309 -0.0921 0.6333 0.0335
-4.750 -0.0354 0.00953 0.00294 -0.0917 0.6225 0.0342
-4.500 -0.0091 0.00945 0.00279 -0.0912 0.6102 0.0348
-4.000 0.0429 0.00928 0.00251 -0.0901 0.5818 0.0375
-3.750 0.0688 0.00923 0.00241 -0.0896 0.5658 0.0392
-3.500 0.0947 0.00922 0.00231 -0.0890 0.5484 0.0407
-3.250 0.1205 0.00918 0.00222 -0.0884 0.5321 0.0432
-3.000 0.1465 0.00915 0.00214 -0.0879 0.5169 0.0464
-2.750 0.1727 0.00914 0.00207 -0.0874 0.5023 0.0495
-2.500 0.1987 0.00911 0.00201 -0.0869 0.4882 0.0546
-2.250 0.2246 0.00909 0.00195 -0.0864 0.4740 0.0609
-2.000 0.2505 0.00907 0.00191 -0.0859 0.4598 0.0706
-1.750 0.2759 0.00902 0.00186 -0.0853 0.4456 0.0893
-1.500 0.3009 0.00892 0.00182 -0.0847 0.4314 0.1236
-1.250 0.3262 0.00889 0.00181 -0.0841 0.4162 0.1514
-1.000 0.3515 0.00889 0.00181 -0.0836 0.4008 0.1745
-0.500 0.4021 0.00893 0.00185 -0.0824 0.3713 0.2203
-0.250 0.4276 0.00892 0.00188 -0.0819 0.3617 0.2527
0.000 0.4524 0.00889 0.00193 -0.0813 0.3510 0.2946
0.250 0.4781 0.00886 0.00196 -0.0808 0.3436 0.3305
0.500 0.5034 0.00884 0.00201 -0.0802 0.3368 0.3686
0.750 0.5290 0.00883 0.00207 -0.0797 0.3317 0.4050
1.000 0.5550 0.00881 0.00212 -0.0792 0.3277 0.4334
1.250 0.5810 0.00883 0.00217 -0.0788 0.3235 0.4586
1.500 0.6064 0.00884 0.00224 -0.0782 0.3193 0.4909
1.750 0.6316 0.00883 0.00231 -0.0777 0.3157 0.5275
2.000 0.6566 0.00877 0.00238 -0.0770 0.3126 0.5774
2.250 0.6795 0.00864 0.00247 -0.0760 0.3090 0.6626
2.500 0.6998 0.00849 0.00258 -0.0743 0.3039 0.7640
2.750 0.7190 0.00831 0.00269 -0.0723 0.2996 0.8703
3.000 0.7985 0.00840 0.00292 -0.0836 0.2950 0.9726
3.250 0.8394 0.00855 0.00303 -0.0864 0.2912 0.9881
3.500 0.8707 0.00870 0.00315 -0.0872 0.2875 0.9981
3.750 0.9004 0.00885 0.00326 -0.0877 0.2837 1.0000
4.000 0.9240 0.00895 0.00335 -0.0868 0.2807 1.0000
4.250 0.9473 0.00907 0.00345 -0.0858 0.2769 1.0000
4.500 0.9703 0.00921 0.00356 -0.0848 0.2728 1.0000
4.750 0.9930 0.00936 0.00369 -0.0838 0.2686 1.0000
5.000 1.0166 0.00948 0.00380 -0.0829 0.2653 1.0000
5.250 1.0395 0.00962 0.00392 -0.0819 0.2596 1.0000
5.500 1.0615 0.00981 0.00407 -0.0808 0.2536 1.0000
5.750 1.0844 0.00995 0.00421 -0.0798 0.2484 1.0000
6.000 1.1061 0.01016 0.00436 -0.0787 0.2408 1.0000
6.250 1.1279 0.01035 0.00453 -0.0775 0.2328 1.0000
6.500 1.1484 0.01061 0.00473 -0.0762 0.2217 1.0000
6.750 1.1668 0.01096 0.00498 -0.0745 0.2045 1.0000
7.000 1.1844 0.01134 0.00528 -0.0727 0.1896 1.0000
7.250 1.2025 0.01166 0.00555 -0.0709 0.1806 1.0000
7.500 1.2196 0.01196 0.00582 -0.0690 0.1741 1.0000
7.750 1.2368 0.01225 0.00609 -0.0670 0.1687 1.0000
8.000 1.2536 0.01256 0.00638 -0.0651 0.1628 1.0000
8.250 1.2706 0.01290 0.00669 -0.0632 0.1580 1.0000
8.500 1.2889 0.01318 0.00698 -0.0616 0.1545 1.0000
8.750 1.3080 0.01344 0.00726 -0.0602 0.1517 1.0000
9.000 1.3269 0.01372 0.00755 -0.0588 0.1495 1.0000
9.250 1.3444 0.01408 0.00790 -0.0572 0.1458 1.0000
9.500 1.3620 0.01444 0.00827 -0.0557 0.1428 1.0000
9.750 1.3803 0.01478 0.00863 -0.0543 0.1404 1.0000
10.000 1.3992 0.01509 0.00896 -0.0530 0.1380 1.0000
10.250 1.4171 0.01546 0.00935 -0.0517 0.1352 1.0000
10.500 1.4335 0.01591 0.00979 -0.0502 0.1310 1.0000
10.750 1.4495 0.01640 0.01029 -0.0486 0.1274 1.0000
11.000 1.4672 0.01681 0.01073 -0.0474 0.1239 1.0000
11.250 1.4817 0.01740 0.01129 -0.0458 0.1178 1.0000
11.500 1.4950 0.01808 0.01195 -0.0442 0.1096 1.0000
11.750 1.5045 0.01900 0.01280 -0.0421 0.0979 1.0000
12.000 1.4934 0.02120 0.01478 -0.0381 0.0661 1.0000
12.250 1.4678 0.02463 0.01801 -0.0334 0.0296 1.0000
12.500 1.4644 0.02680 0.02016 -0.0312 0.0177 1.0000
12.750 1.4709 0.02832 0.02172 -0.0300 0.0154 1.0000
13.000 1.4773 0.02990 0.02335 -0.0290 0.0138 1.0000
13.250 1.4850 0.03145 0.02495 -0.0281 0.0130 1.0000
13.500 1.4917 0.03313 0.02669 -0.0273 0.0124 1.0000
13.750 1.4958 0.03510 0.02872 -0.0266 0.0115 1.0000
14.000 1.5001 0.03712 0.03080 -0.0260 0.0111 1.0000
14.250 1.5049 0.03913 0.03288 -0.0255 0.0107 1.0000
14.500 1.5085 0.04135 0.03516 -0.0251 0.0104 1.0000
14.750 1.5107 0.04373 0.03761 -0.0248 0.0101 1.0000
15.000 1.5108 0.04641 0.04037 -0.0246 0.0097 1.0000
15.250 1.5099 0.04930 0.04334 -0.0246 0.0094 1.0000
15.500 1.5073 0.05246 0.04657 -0.0247 0.0091 1.0000
15.750 1.5034 0.05583 0.05002 -0.0249 0.0087 1.0000
16.000 1.4993 0.05934 0.05363 -0.0252 0.0086 1.0000
16.250 1.4946 0.06301 0.05739 -0.0257 0.0085 1.0000
16.500 1.4894 0.06676 0.06123 -0.0263 0.0082 1.0000
16.750 1.4825 0.07079 0.06534 -0.0270 0.0081 1.0000
17.000 1.4731 0.07524 0.06990 -0.0279 0.0081 1.0000
17.250 1.4641 0.07968 0.07443 -0.0289 0.0078 1.0000
17.500 1.4532 0.08439 0.07924 -0.0299 0.0077 1.0000
17.750 1.4421 0.08920 0.08414 -0.0311 0.0076 1.0000
18.000 1.4294 0.09432 0.08936 -0.0324 0.0075 1.0000
18.250 1.4180 0.09926 0.09439 -0.0337 0.0073 1.0000
18.500 1.4057 0.10436 0.09959 -0.0352 0.0073 1.0000
18.750 1.3928 0.10964 0.10495 -0.0368 0.0071 1.0000
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