GOE 401 AIRFOIL (goe401-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 401 AIRFOIL (goe401-il) Reynolds number: 500,000 Max Cl/Cd: 100.77 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe401-il-500000-n5.txt Download as CSV file: xf-goe401-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 401 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3436 0.10242 0.10007 -0.0190 1.0000 0.0136
-9.000 -0.3403 0.09937 0.09704 -0.0198 1.0000 0.0140
-8.750 -0.3439 0.09488 0.09257 -0.0215 1.0000 0.0150
-8.500 -0.3394 0.09259 0.09031 -0.0217 1.0000 0.0151
-8.250 -0.3331 0.09092 0.08866 -0.0215 1.0000 0.0155
-8.000 -0.3288 0.08909 0.08686 -0.0213 1.0000 0.0160
-7.750 -0.3309 0.08658 0.08439 -0.0210 1.0000 0.0160
-7.500 -0.3239 0.08357 0.08140 -0.0233 0.9979 0.0163
-7.250 -0.3054 0.07938 0.07721 -0.0289 0.9881 0.0167
-7.000 -0.2909 0.07546 0.07328 -0.0334 0.9693 0.0171
-6.500 -0.2123 0.06581 0.06350 -0.0536 0.9281 0.0200
-6.250 -0.1556 0.05961 0.05713 -0.0683 0.9070 0.0205
-6.000 -0.1183 0.05492 0.05222 -0.0770 0.8742 0.0208
-5.750 -0.0960 0.05064 0.04772 -0.0816 0.8472 0.0221
-5.500 -0.0753 0.04515 0.04198 -0.0859 0.8269 0.0229
-5.250 -0.0574 0.04444 0.04121 -0.0854 0.8096 0.0235
-5.000 -0.0377 0.04267 0.03932 -0.0859 0.7937 0.0239
-4.750 -0.0162 0.03931 0.03577 -0.0873 0.7790 0.0238
-4.500 0.0052 0.03744 0.03377 -0.0877 0.7641 0.0244
-4.000 0.0507 0.03239 0.02833 -0.0887 0.7359 0.0254
-3.750 0.0741 0.02948 0.02520 -0.0889 0.7236 0.0253
-3.500 0.0975 0.02674 0.02221 -0.0887 0.7108 0.0253
-3.250 0.1208 0.02386 0.01904 -0.0883 0.6982 0.0253
-3.000 0.1439 0.02090 0.01575 -0.0875 0.6846 0.0258
-2.750 0.1652 0.01650 0.01072 -0.0862 0.6720 0.0259
-2.500 0.1890 0.01489 0.00874 -0.0853 0.6569 0.0261
-2.250 0.2135 0.01394 0.00749 -0.0845 0.6399 0.0265
-2.000 0.2383 0.01325 0.00655 -0.0837 0.6199 0.0267
-1.750 0.2633 0.01272 0.00579 -0.0829 0.5979 0.0270
-1.500 0.2881 0.01232 0.00518 -0.0822 0.5741 0.0272
-1.000 0.3377 0.01185 0.00431 -0.0806 0.5186 0.0277
-0.750 0.3628 0.01177 0.00407 -0.0799 0.4947 0.0280
-0.500 0.3877 0.01146 0.00361 -0.0792 0.4752 0.0283
-0.250 0.4127 0.01116 0.00320 -0.0785 0.4600 0.0286
0.000 0.4378 0.01090 0.00287 -0.0779 0.4481 0.0289
0.250 0.4629 0.01073 0.00263 -0.0772 0.4374 0.0293
0.500 0.4884 0.01058 0.00246 -0.0766 0.4284 0.0298
0.750 0.5139 0.01050 0.00234 -0.0760 0.4204 0.0304
1.000 0.5397 0.01043 0.00225 -0.0755 0.4131 0.0311
1.500 0.5915 0.01037 0.00215 -0.0744 0.4006 0.0326
1.750 0.6174 0.01037 0.00213 -0.0739 0.3943 0.0333
2.000 0.6433 0.01039 0.00213 -0.0734 0.3888 0.0344
2.250 0.6695 0.01040 0.00214 -0.0730 0.3828 0.0357
2.500 0.6953 0.01044 0.00215 -0.0725 0.3769 0.0379
2.750 0.7214 0.01046 0.00219 -0.0720 0.3718 0.0412
3.000 0.7471 0.01042 0.00228 -0.0715 0.3661 0.0857
3.250 0.7725 0.01048 0.00239 -0.0710 0.3599 0.1232
3.500 0.7986 0.01051 0.00250 -0.0706 0.3545 0.1524
3.750 0.8242 0.01053 0.00263 -0.0701 0.3490 0.1949
4.250 0.9141 0.00941 0.00303 -0.0785 0.3243 1.0000
4.500 0.9388 0.00958 0.00316 -0.0778 0.3154 1.0000
4.750 0.9636 0.00973 0.00329 -0.0771 0.3083 1.0000
5.000 0.9880 0.00992 0.00345 -0.0764 0.2999 1.0000
5.250 1.0126 0.01009 0.00361 -0.0757 0.2917 1.0000
5.500 1.0366 0.01030 0.00378 -0.0750 0.2814 1.0000
5.750 1.0603 0.01054 0.00397 -0.0742 0.2696 1.0000
6.000 1.0843 0.01076 0.00419 -0.0734 0.2592 1.0000
6.250 1.1078 0.01101 0.00441 -0.0726 0.2492 1.0000
6.500 1.1308 0.01130 0.00466 -0.0717 0.2360 1.0000
6.750 1.1530 0.01167 0.00496 -0.0707 0.2179 1.0000
7.000 1.1752 0.01202 0.00526 -0.0698 0.2028 1.0000
7.250 1.1966 0.01245 0.00561 -0.0687 0.1840 1.0000
7.500 1.2167 0.01299 0.00601 -0.0675 0.1586 1.0000
7.750 1.2346 0.01372 0.00656 -0.0659 0.1239 1.0000
8.000 1.2448 0.01513 0.00758 -0.0633 0.0628 1.0000
8.250 1.2646 0.01565 0.00810 -0.0620 0.0555 1.0000
8.500 1.2849 0.01611 0.00858 -0.0608 0.0497 1.0000
8.750 1.3048 0.01659 0.00909 -0.0596 0.0445 1.0000
9.000 1.3241 0.01710 0.00962 -0.0583 0.0392 1.0000
9.250 1.3420 0.01768 0.01019 -0.0568 0.0305 1.0000
9.750 1.3728 0.01915 0.01158 -0.0531 0.0169 1.0000
10.000 1.3881 0.01982 0.01231 -0.0513 0.0151 1.0000
10.250 1.4032 0.02046 0.01302 -0.0494 0.0141 1.0000
10.500 1.4154 0.02115 0.01378 -0.0471 0.0132 1.0000
10.750 1.4245 0.02193 0.01462 -0.0442 0.0124 1.0000
11.000 1.4314 0.02285 0.01562 -0.0412 0.0116 1.0000
11.250 1.4404 0.02369 0.01654 -0.0388 0.0112 1.0000
11.500 1.4491 0.02457 0.01752 -0.0364 0.0107 1.0000
11.750 1.4563 0.02561 0.01865 -0.0341 0.0102 1.0000
12.000 1.4619 0.02682 0.01995 -0.0319 0.0098 1.0000
12.250 1.4664 0.02820 0.02142 -0.0300 0.0095 1.0000
12.500 1.4696 0.02980 0.02312 -0.0282 0.0092 1.0000
12.750 1.4707 0.03173 0.02514 -0.0267 0.0090 1.0000
13.000 1.4694 0.03406 0.02758 -0.0256 0.0087 1.0000
13.250 1.4640 0.03700 0.03065 -0.0247 0.0085 1.0000
13.500 1.4619 0.03982 0.03359 -0.0244 0.0083 1.0000
13.750 1.4604 0.04272 0.03661 -0.0243 0.0082 1.0000
14.000 1.4581 0.04587 0.03988 -0.0245 0.0080 1.0000
14.250 1.4532 0.04947 0.04361 -0.0249 0.0079 1.0000
14.500 1.4460 0.05353 0.04779 -0.0257 0.0078 1.0000
14.750 1.4405 0.05748 0.05186 -0.0266 0.0077 1.0000
15.000 1.4325 0.06188 0.05639 -0.0277 0.0076 1.0000
15.250 1.4254 0.06625 0.06087 -0.0289 0.0074 1.0000
15.500 1.4165 0.07095 0.06568 -0.0302 0.0073 1.0000
15.750 1.4087 0.07555 0.07038 -0.0316 0.0072 1.0000
16.000 1.3981 0.08062 0.07557 -0.0332 0.0072 1.0000
16.250 1.3882 0.08563 0.08068 -0.0348 0.0070 1.0000
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Polar data table (+)
Polar graphs
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