GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 457 AIRFOIL (goe457-il) Reynolds number: 200,000 Max Cl/Cd: 72.9 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe457-il-200000-n5.txt Download as CSV file: xf-goe457-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 457 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3666 0.08794 0.08468 -0.0203 1.0000 0.0176
-7.250 -0.3795 0.08611 0.08292 -0.0179 1.0000 0.0175
-7.000 -0.3871 0.08341 0.08028 -0.0174 1.0000 0.0172
-6.750 -0.3656 0.07842 0.07526 -0.0246 0.9958 0.0178
-6.500 -0.3406 0.07307 0.06988 -0.0329 0.9905 0.0188
-6.250 -0.3118 0.06649 0.06324 -0.0431 0.9856 0.0196
-6.000 -0.2848 0.06003 0.05669 -0.0517 0.9796 0.0197
-5.750 -0.2511 0.05163 0.04810 -0.0624 0.9745 0.0202
-5.500 -0.2179 0.04268 0.03884 -0.0715 0.9687 0.0218
-5.250 -0.1855 0.04141 0.03750 -0.0744 0.9656 0.0232
-5.000 -0.1573 0.03606 0.03184 -0.0780 0.9590 0.0245
-4.750 -0.1220 0.02917 0.02430 -0.0825 0.9547 0.0270
-4.500 -0.0899 0.02469 0.01901 -0.0843 0.9498 0.0292
-4.250 -0.0629 0.02186 0.01582 -0.0852 0.9443 0.0310
-4.000 -0.0291 0.02090 0.01470 -0.0868 0.9407 0.0334
-3.750 0.0049 0.01921 0.01264 -0.0881 0.9374 0.0351
-3.500 0.0322 0.01798 0.01112 -0.0878 0.9306 0.0367
-3.250 0.0673 0.01692 0.00975 -0.0891 0.9264 0.0387
-3.000 0.1018 0.01592 0.00852 -0.0902 0.9215 0.0394
-2.750 0.1313 0.01500 0.00746 -0.0902 0.9139 0.0401
-2.500 0.1677 0.01399 0.00636 -0.0918 0.9088 0.0415
-2.250 0.1954 0.01349 0.00584 -0.0916 0.8984 0.0436
-2.000 0.2272 0.01296 0.00528 -0.0921 0.8886 0.0450
-1.750 0.2595 0.01245 0.00472 -0.0927 0.8773 0.0462
-1.500 0.2891 0.01204 0.00426 -0.0927 0.8626 0.0475
-1.250 0.3175 0.01171 0.00387 -0.0925 0.8428 0.0494
-1.000 0.3481 0.01140 0.00348 -0.0926 0.8159 0.0519
-0.750 0.3821 0.01111 0.00309 -0.0934 0.7743 0.0580
-0.500 0.4135 0.01101 0.00275 -0.0936 0.7229 0.0704
-0.250 0.4393 0.01103 0.00257 -0.0928 0.6757 0.0970
0.000 0.4625 0.01093 0.00253 -0.0918 0.6336 0.1719
0.500 0.5066 0.01062 0.00264 -0.0895 0.5726 0.4397
1.000 0.5765 0.00989 0.00274 -0.0922 0.5322 1.0000
1.250 0.6011 0.01011 0.00280 -0.0914 0.5178 1.0000
1.500 0.6259 0.01033 0.00288 -0.0906 0.5049 1.0000
2.000 0.6761 0.01073 0.00308 -0.0893 0.4816 1.0000
2.250 0.7014 0.01092 0.00320 -0.0887 0.4712 1.0000
2.500 0.7265 0.01113 0.00332 -0.0880 0.4608 1.0000
2.750 0.7517 0.01132 0.00347 -0.0874 0.4499 1.0000
3.000 0.7770 0.01151 0.00362 -0.0868 0.4394 1.0000
3.250 0.8019 0.01172 0.00378 -0.0862 0.4286 1.0000
3.500 0.8265 0.01194 0.00394 -0.0855 0.4164 1.0000
3.750 0.8511 0.01215 0.00411 -0.0848 0.4032 1.0000
4.000 0.8756 0.01237 0.00429 -0.0840 0.3892 1.0000
4.250 0.8997 0.01260 0.00449 -0.0833 0.3744 1.0000
4.500 0.9235 0.01285 0.00469 -0.0825 0.3585 1.0000
4.750 0.9472 0.01312 0.00490 -0.0817 0.3411 1.0000
5.000 0.9709 0.01339 0.00515 -0.0809 0.3239 1.0000
5.250 0.9945 0.01368 0.00541 -0.0801 0.3085 1.0000
5.500 1.0182 0.01398 0.00569 -0.0793 0.2951 1.0000
5.750 1.0417 0.01429 0.00599 -0.0785 0.2816 1.0000
6.000 1.0650 0.01462 0.00633 -0.0777 0.2666 1.0000
6.250 1.0879 0.01498 0.00668 -0.0768 0.2501 1.0000
6.500 1.1102 0.01538 0.00706 -0.0759 0.2303 1.0000
6.750 1.1315 0.01588 0.00749 -0.0749 0.2048 1.0000
7.000 1.1505 0.01660 0.00802 -0.0736 0.1639 1.0000
7.250 1.1673 0.01755 0.00871 -0.0720 0.1269 1.0000
7.500 1.1858 0.01834 0.00940 -0.0707 0.1082 1.0000
7.750 1.2050 0.01902 0.01005 -0.0694 0.0960 1.0000
8.000 1.2243 0.01966 0.01068 -0.0681 0.0865 1.0000
8.250 1.2444 0.02020 0.01129 -0.0670 0.0779 1.0000
8.500 1.2636 0.02080 0.01191 -0.0657 0.0706 1.0000
8.750 1.2816 0.02148 0.01256 -0.0643 0.0604 1.0000
9.000 1.2992 0.02215 0.01324 -0.0628 0.0494 1.0000
9.250 1.3105 0.02332 0.01423 -0.0606 0.0221 1.0000
9.500 1.3204 0.02453 0.01546 -0.0579 0.0177 1.0000
9.750 1.3295 0.02564 0.01671 -0.0551 0.0157 1.0000
10.000 1.3373 0.02680 0.01803 -0.0522 0.0140 1.0000
10.250 1.3470 0.02782 0.01919 -0.0497 0.0134 1.0000
10.500 1.3552 0.02894 0.02049 -0.0471 0.0128 1.0000
10.750 1.3617 0.03020 0.02192 -0.0445 0.0124 1.0000
11.000 1.3663 0.03163 0.02352 -0.0418 0.0119 1.0000
11.250 1.3692 0.03320 0.02527 -0.0393 0.0115 1.0000
11.500 1.3697 0.03503 0.02726 -0.0368 0.0110 1.0000
11.750 1.3687 0.03706 0.02946 -0.0347 0.0107 1.0000
12.000 1.3634 0.03962 0.03218 -0.0327 0.0103 1.0000
12.250 1.3546 0.04271 0.03547 -0.0312 0.0099 1.0000
12.500 1.3458 0.04613 0.03905 -0.0304 0.0098 1.0000
12.750 1.3330 0.05038 0.04345 -0.0304 0.0095 1.0000
13.000 1.3282 0.05403 0.04726 -0.0309 0.0094 1.0000
13.250 1.3235 0.05791 0.05130 -0.0317 0.0093 1.0000
13.500 1.3171 0.06223 0.05578 -0.0329 0.0092 1.0000
13.750 1.3098 0.06682 0.06051 -0.0344 0.0091 1.0000
14.000 1.3026 0.07154 0.06537 -0.0360 0.0090 1.0000
14.250 1.2948 0.07639 0.07037 -0.0377 0.0090 1.0000
14.500 1.2866 0.08143 0.07554 -0.0396 0.0088 1.0000
14.750 1.2790 0.08644 0.08069 -0.0415 0.0087 1.0000
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