GOE 113 AIRFOIL (goe113-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 113 AIRFOIL (goe113-il) Reynolds number: 100,000 Max Cl/Cd: 54.32 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe113-il-100000-n5.txt Download as CSV file: xf-goe113-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 113 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.4292 0.09697 0.09224 -0.0110 1.0000 0.0259
-7.500 -0.4258 0.09373 0.08905 -0.0124 1.0000 0.0262
-7.250 -0.4227 0.09050 0.08588 -0.0139 1.0000 0.0265
-7.000 -0.4168 0.08697 0.08240 -0.0165 1.0000 0.0268
-6.750 -0.4093 0.08334 0.07880 -0.0194 1.0000 0.0272
-6.500 -0.4004 0.07966 0.07515 -0.0224 1.0000 0.0281
-6.250 -0.3898 0.07591 0.07141 -0.0256 1.0000 0.0294
-6.000 -0.3754 0.07202 0.06749 -0.0301 1.0000 0.0315
-5.750 -0.3525 0.06808 0.06339 -0.0368 1.0000 0.0329
-5.500 -0.3333 0.06431 0.05946 -0.0399 1.0000 0.0331
-5.250 -0.3152 0.06053 0.05550 -0.0417 1.0000 0.0333
-5.000 -0.2972 0.05672 0.05148 -0.0428 1.0000 0.0333
-4.500 -0.2604 0.04909 0.04351 -0.0439 1.0000 0.0333
-4.000 -0.2201 0.03967 0.03373 -0.0441 1.0000 0.0229
-3.500 -0.1805 0.03361 0.02735 -0.0446 1.0000 0.0264
-3.250 -0.1565 0.03108 0.02450 -0.0445 1.0000 0.0288
-3.000 -0.1307 0.02827 0.02126 -0.0442 1.0000 0.0289
-2.750 -0.0964 0.02545 0.01785 -0.0453 0.9973 0.0298
-2.500 -0.0551 0.02301 0.01479 -0.0477 0.9912 0.0352
-2.250 -0.0152 0.02097 0.01236 -0.0500 0.9845 0.0382
-2.000 0.0242 0.01940 0.01039 -0.0521 0.9769 0.0453
-1.750 0.0625 0.01797 0.00878 -0.0542 0.9684 0.0486
-1.500 0.1002 0.01720 0.00783 -0.0561 0.9579 0.0554
-1.250 0.1362 0.01626 0.00682 -0.0577 0.9462 0.0554
-1.000 0.1710 0.01554 0.00601 -0.0590 0.9322 0.0555
-0.750 0.2058 0.01499 0.00535 -0.0603 0.9170 0.0560
-0.500 0.2410 0.01455 0.00479 -0.0616 0.9008 0.0572
-0.250 0.2743 0.01419 0.00429 -0.0625 0.8819 0.0604
0.000 0.3078 0.01392 0.00392 -0.0633 0.8629 0.0678
0.250 0.3398 0.01122 0.00374 -0.0637 0.8457 1.0000
0.500 0.3703 0.01127 0.00350 -0.0638 0.8228 1.0000
0.750 0.3997 0.01135 0.00334 -0.0637 0.7995 1.0000
1.000 0.4278 0.01147 0.00325 -0.0634 0.7756 1.0000
1.250 0.4550 0.01161 0.00323 -0.0630 0.7525 1.0000
1.500 0.4821 0.01178 0.00325 -0.0626 0.7311 1.0000
1.750 0.5086 0.01196 0.00330 -0.0622 0.7104 1.0000
2.000 0.5349 0.01215 0.00338 -0.0617 0.6894 1.0000
2.250 0.5608 0.01235 0.00350 -0.0611 0.6670 1.0000
2.500 0.5866 0.01256 0.00361 -0.0605 0.6450 1.0000
2.750 0.6123 0.01277 0.00375 -0.0600 0.6228 1.0000
3.000 0.6379 0.01300 0.00390 -0.0594 0.6000 1.0000
3.250 0.6635 0.01322 0.00414 -0.0588 0.5766 1.0000
3.500 0.6892 0.01346 0.00436 -0.0583 0.5560 1.0000
3.750 0.7150 0.01369 0.00464 -0.0579 0.5348 1.0000
4.000 0.7404 0.01396 0.00491 -0.0574 0.5116 1.0000
4.250 0.7657 0.01423 0.00527 -0.0568 0.4842 1.0000
4.500 0.7903 0.01455 0.00559 -0.0562 0.4455 1.0000
4.750 0.8101 0.01529 0.00582 -0.0548 0.3391 1.0000
5.000 0.8309 0.01623 0.00635 -0.0539 0.2681 1.0000
5.250 0.8528 0.01711 0.00708 -0.0532 0.2233 1.0000
5.500 0.8741 0.01810 0.00775 -0.0525 0.1537 1.0000
5.750 0.8953 0.01919 0.00855 -0.0516 0.0680 1.0000
6.000 0.9117 0.02113 0.01005 -0.0501 0.0244 1.0000
6.250 0.9327 0.02240 0.01148 -0.0489 0.0201 1.0000
6.500 0.9543 0.02352 0.01290 -0.0479 0.0190 1.0000
6.750 0.9746 0.02480 0.01455 -0.0466 0.0182 1.0000
7.000 0.9933 0.02622 0.01623 -0.0452 0.0169 1.0000
7.250 1.0102 0.02778 0.01801 -0.0438 0.0153 1.0000
7.500 1.0258 0.02951 0.01993 -0.0421 0.0145 1.0000
7.750 1.0415 0.03142 0.02198 -0.0404 0.0141 1.0000
8.000 1.0585 0.03351 0.02422 -0.0388 0.0139 1.0000
8.250 1.0769 0.03584 0.02672 -0.0374 0.0137 1.0000
8.500 1.0955 0.03838 0.02950 -0.0360 0.0137 1.0000
8.750 1.1129 0.04115 0.03258 -0.0346 0.0137 1.0000
9.000 1.1269 0.04413 0.03590 -0.0330 0.0136 1.0000
9.250 1.1366 0.04731 0.03953 -0.0313 0.0133 1.0000
9.500 1.1415 0.05085 0.04340 -0.0295 0.0128 1.0000
9.750 1.1418 0.05461 0.04750 -0.0275 0.0125 1.0000
10.000 1.1376 0.05847 0.05169 -0.0254 0.0123 1.0000
10.250 1.1288 0.06199 0.05551 -0.0231 0.0122 1.0000
10.500 1.1168 0.06526 0.05904 -0.0209 0.0122 1.0000
10.750 1.1036 0.06878 0.06281 -0.0198 0.0122 1.0000
11.000 1.0894 0.07277 0.06704 -0.0200 0.0122 1.0000
11.250 1.0747 0.07734 0.07183 -0.0215 0.0123 1.0000
11.500 1.0601 0.08249 0.07719 -0.0241 0.0124 1.0000
11.750 1.0447 0.08845 0.08335 -0.0279 0.0125 1.0000
12.000 1.0291 0.09525 0.09035 -0.0326 0.0127 1.0000
12.250 1.0122 0.10325 0.09853 -0.0385 0.0130 1.0000
12.500 0.9843 0.11671 0.11221 -0.0487 0.0144 1.0000
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Polar data table (+)
Polar graphs
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