GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 403 AIRFOIL (goe403-il) Reynolds number: 100,000 Max Cl/Cd: 57.6 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe403-il-100000-n5.txt Download as CSV file: xf-goe403-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 403 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3492 0.10342 0.09873 -0.0304 1.0000 0.0321
-8.000 -0.3489 0.10068 0.09607 -0.0309 1.0000 0.0321
-7.750 -0.3486 0.09782 0.09328 -0.0311 1.0000 0.0322
-7.500 -0.3457 0.09464 0.09017 -0.0319 1.0000 0.0321
-7.250 -0.3423 0.09137 0.08696 -0.0329 1.0000 0.0321
-7.000 -0.3341 0.08679 0.08237 -0.0269 1.0000 0.0296
-6.750 -0.3333 0.08387 0.07953 -0.0271 1.0000 0.0277
-6.500 -0.3334 0.08081 0.07656 -0.0280 1.0000 0.0264
-6.250 -0.3331 0.07782 0.07364 -0.0289 1.0000 0.0252
-5.250 -0.2653 0.05770 0.05342 -0.0512 0.9869 0.0220
-5.000 -0.2349 0.05536 0.05097 -0.0551 0.9788 0.0254
-4.750 -0.1962 0.04961 0.04500 -0.0631 0.9706 0.0270
-4.500 -0.1548 0.04296 0.03804 -0.0710 0.9633 0.0275
-4.250 -0.1126 0.03553 0.03008 -0.0779 0.9563 0.0291
-4.000 -0.0732 0.02849 0.02217 -0.0828 0.9497 0.0335
-3.750 -0.0377 0.02572 0.01891 -0.0852 0.9429 0.0384
-3.500 -0.0027 0.02349 0.01613 -0.0872 0.9361 0.0469
-3.250 0.0328 0.02172 0.01365 -0.0886 0.9288 0.0557
-3.000 0.0649 0.02001 0.01165 -0.0896 0.9208 0.0592
-2.750 0.0998 0.01878 0.01008 -0.0908 0.9136 0.0639
-2.500 0.1313 0.01780 0.00875 -0.0913 0.9040 0.0684
-2.250 0.1642 0.01726 0.00813 -0.0923 0.8952 0.0761
-2.000 0.1971 0.01652 0.00719 -0.0930 0.8860 0.0810
-1.750 0.2275 0.01585 0.00645 -0.0933 0.8753 0.0860
-1.500 0.2583 0.01533 0.00582 -0.0936 0.8646 0.0952
-1.250 0.2891 0.01487 0.00530 -0.0939 0.8537 0.1108
-1.000 0.3195 0.01447 0.00492 -0.0942 0.8423 0.1331
-0.750 0.3486 0.01419 0.00466 -0.0943 0.8302 0.1670
-0.500 0.3770 0.01387 0.00449 -0.0943 0.8169 0.2237
-0.250 0.4045 0.01337 0.00436 -0.0942 0.8034 0.3418
0.000 0.4417 0.01184 0.00414 -0.0956 0.7899 1.0000
0.250 0.4687 0.01192 0.00401 -0.0951 0.7748 1.0000
0.500 0.4952 0.01202 0.00392 -0.0946 0.7593 1.0000
0.750 0.5209 0.01212 0.00389 -0.0939 0.7419 1.0000
1.000 0.5468 0.01223 0.00388 -0.0933 0.7244 1.0000
1.250 0.5726 0.01234 0.00387 -0.0927 0.7065 1.0000
1.500 0.5986 0.01246 0.00387 -0.0921 0.6890 1.0000
1.750 0.6243 0.01260 0.00394 -0.0915 0.6710 1.0000
2.000 0.6501 0.01275 0.00401 -0.0909 0.6532 1.0000
2.250 0.6759 0.01293 0.00411 -0.0903 0.6365 1.0000
2.500 0.7016 0.01313 0.00424 -0.0898 0.6207 1.0000
2.750 0.7273 0.01335 0.00445 -0.0892 0.6059 1.0000
3.000 0.7530 0.01359 0.00467 -0.0887 0.5921 1.0000
3.250 0.7787 0.01385 0.00494 -0.0882 0.5790 1.0000
3.500 0.8043 0.01413 0.00528 -0.0877 0.5663 1.0000
3.750 0.8260 0.01444 0.00541 -0.0862 0.5311 1.0000
4.000 0.8492 0.01475 0.00570 -0.0852 0.5052 1.0000
4.250 0.8703 0.01511 0.00596 -0.0837 0.4641 1.0000
4.500 0.8904 0.01555 0.00623 -0.0822 0.4088 1.0000
4.750 0.9075 0.01638 0.00663 -0.0803 0.3079 1.0000
5.000 0.9083 0.01982 0.00827 -0.0771 0.0322 1.0000
5.250 0.9295 0.02069 0.00923 -0.0758 0.0263 1.0000
5.500 0.9493 0.02169 0.01042 -0.0745 0.0221 1.0000
5.750 0.9675 0.02287 0.01185 -0.0728 0.0200 1.0000
6.000 0.9857 0.02397 0.01321 -0.0712 0.0193 1.0000
6.250 1.0017 0.02521 0.01475 -0.0694 0.0188 1.0000
6.500 1.0155 0.02658 0.01632 -0.0672 0.0183 1.0000
6.750 1.0285 0.02800 0.01788 -0.0650 0.0172 1.0000
7.000 1.0415 0.02952 0.01950 -0.0629 0.0160 1.0000
7.250 1.0565 0.03121 0.02124 -0.0610 0.0154 1.0000
7.500 1.0760 0.03312 0.02320 -0.0595 0.0153 1.0000
7.750 1.0999 0.03528 0.02546 -0.0586 0.0152 1.0000
8.000 1.1253 0.03768 0.02804 -0.0578 0.0154 1.0000
8.250 1.1497 0.04030 0.03091 -0.0569 0.0157 1.0000
8.500 1.1713 0.04322 0.03423 -0.0556 0.0162 1.0000
8.750 1.1881 0.04621 0.03758 -0.0540 0.0165 1.0000
9.000 1.2005 0.04922 0.04096 -0.0521 0.0166 1.0000
9.250 1.2085 0.05221 0.04432 -0.0499 0.0162 1.0000
9.500 1.2132 0.05534 0.04782 -0.0476 0.0162 1.0000
9.750 1.2138 0.05855 0.05137 -0.0451 0.0162 1.0000
10.000 1.2103 0.06177 0.05491 -0.0425 0.0163 1.0000
10.250 1.2015 0.06491 0.05832 -0.0396 0.0166 1.0000
10.500 1.1901 0.06820 0.06186 -0.0370 0.0170 1.0000
10.750 1.1768 0.07172 0.06561 -0.0353 0.0173 1.0000
11.000 1.1621 0.07565 0.06975 -0.0344 0.0176 1.0000
11.250 1.1463 0.07993 0.07424 -0.0344 0.0178 1.0000
11.500 1.1301 0.08464 0.07913 -0.0354 0.0180 1.0000
11.750 1.1131 0.08982 0.08449 -0.0372 0.0182 1.0000
12.000 1.0955 0.09557 0.09041 -0.0399 0.0182 1.0000
12.250 1.0779 0.10189 0.09689 -0.0434 0.0183 1.0000
12.500 1.0608 0.10874 0.10388 -0.0478 0.0184 1.0000
12.750 1.0443 0.11617 0.11141 -0.0526 0.0185 1.0000
13.000 1.0295 0.12397 0.11931 -0.0577 0.0187 1.0000
13.250 1.0178 0.13176 0.12715 -0.0626 0.0190 1.0000
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Polar data table (+)
Polar graphs
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