GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 507 AIRFOIL (goe507-il) Reynolds number: 50,000 Max Cl/Cd: 37.65 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe507-il-50000.txt Download as CSV file: xf-goe507-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 507 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4037 0.09850 0.09124 -0.0191 1.0000 0.2610
-8.000 -0.3987 0.09499 0.08779 -0.0186 1.0000 0.2685
-7.750 -0.4163 0.09422 0.08717 -0.0183 1.0000 0.2783
-7.500 -0.4018 0.09023 0.08318 -0.0168 1.0000 0.2918
-7.250 -0.3971 0.08717 0.08019 -0.0153 1.0000 0.3045
-7.000 -0.4383 0.08773 0.08102 -0.0143 1.0000 0.3106
-6.750 -0.4348 0.08480 0.07815 -0.0120 1.0000 0.3261
-6.500 -0.4330 0.08200 0.07542 -0.0096 1.0000 0.3416
-6.250 -0.4323 0.07934 0.07281 -0.0070 1.0000 0.3571
-6.000 -0.4401 0.07735 0.07092 -0.0043 1.0000 0.3733
-5.750 -0.4192 0.07363 0.06720 -0.0001 1.0000 0.3983
-5.500 -0.4434 0.07292 0.06663 0.0035 1.0000 0.4208
-5.250 -0.4403 0.07056 0.06434 0.0084 1.0000 0.4520
-4.500 -0.3048 0.05928 0.05277 0.0192 1.0000 0.6861
-4.250 -0.1618 0.05097 0.04401 0.0063 1.0000 0.8486
-4.000 -0.4087 0.05021 0.04328 -0.0154 1.0000 0.3143
-3.750 -0.3553 0.04052 0.03177 -0.0291 1.0000 0.2006
-3.500 -0.3352 0.03787 0.02889 -0.0288 1.0000 0.1970
-3.250 -0.3137 0.03564 0.02626 -0.0286 1.0000 0.1970
-3.000 -0.2913 0.03374 0.02392 -0.0284 1.0000 0.1990
-2.750 -0.2682 0.03199 0.02178 -0.0280 1.0000 0.1993
-2.500 -0.2443 0.03049 0.01986 -0.0276 1.0000 0.2004
-2.250 -0.2216 0.02919 0.01837 -0.0270 1.0000 0.2041
-2.000 -0.1996 0.02827 0.01732 -0.0263 1.0000 0.2118
-1.750 -0.1763 0.02736 0.01613 -0.0257 1.0000 0.2186
-1.500 -0.1529 0.02650 0.01521 -0.0252 1.0000 0.2259
-1.250 -0.1301 0.02575 0.01431 -0.0244 1.0000 0.2358
-1.000 -0.1060 0.02512 0.01365 -0.0239 1.0000 0.2522
-0.750 -0.0803 0.02446 0.01307 -0.0237 1.0000 0.2831
-0.500 -0.0535 0.02319 0.01235 -0.0235 1.0000 0.3660
-0.250 -0.0119 0.02062 0.01164 -0.0253 1.0000 1.0000
0.000 0.0072 0.02104 0.01171 -0.0245 1.0000 1.0000
0.250 0.0254 0.02151 0.01191 -0.0237 1.0000 1.0000
0.500 0.0432 0.02203 0.01223 -0.0230 1.0000 1.0000
0.750 0.0605 0.02260 0.01263 -0.0223 1.0000 1.0000
1.000 0.0774 0.02324 0.01313 -0.0218 1.0000 1.0000
1.250 0.0939 0.02393 0.01371 -0.0212 1.0000 1.0000
1.500 0.1172 0.02484 0.01452 -0.0222 0.9968 1.0000
1.750 0.1716 0.02636 0.01594 -0.0289 0.9788 1.0000
2.000 0.2217 0.02769 0.01721 -0.0345 0.9602 1.0000
2.250 0.2735 0.02897 0.01847 -0.0401 0.9417 1.0000
2.500 0.3163 0.02997 0.01947 -0.0439 0.9216 1.0000
2.750 0.3587 0.03086 0.02041 -0.0473 0.9009 1.0000
3.000 0.4078 0.03167 0.02128 -0.0514 0.8806 1.0000
3.250 0.4473 0.03232 0.02201 -0.0537 0.8590 1.0000
3.500 0.4882 0.03283 0.02264 -0.0559 0.8374 1.0000
3.750 0.5401 0.03305 0.02302 -0.0593 0.8176 1.0000
4.000 0.5709 0.03348 0.02359 -0.0596 0.7953 1.0000
4.250 0.6165 0.03345 0.02376 -0.0615 0.7747 1.0000
4.500 0.6712 0.03291 0.02347 -0.0640 0.7560 1.0000
4.750 0.6970 0.03317 0.02391 -0.0629 0.7327 1.0000
5.000 0.7572 0.03118 0.02220 -0.0637 0.7102 1.0000
5.250 0.8069 0.02859 0.01984 -0.0619 0.6790 1.0000
5.500 0.8387 0.02719 0.01857 -0.0589 0.6455 1.0000
5.750 0.8697 0.02578 0.01723 -0.0558 0.6081 1.0000
6.000 0.8953 0.02479 0.01624 -0.0523 0.5647 1.0000
6.250 0.9164 0.02446 0.01582 -0.0488 0.5158 1.0000
6.500 0.9276 0.02464 0.01575 -0.0440 0.4461 1.0000
6.750 0.9250 0.02578 0.01613 -0.0376 0.3376 1.0000
7.000 0.9318 0.02811 0.01752 -0.0338 0.2547 1.0000
7.250 0.9517 0.03009 0.01917 -0.0322 0.2149 1.0000
7.500 0.9775 0.03204 0.02091 -0.0315 0.1908 1.0000
7.750 1.0029 0.03398 0.02286 -0.0307 0.1728 1.0000
8.000 1.0288 0.03613 0.02507 -0.0301 0.1594 1.0000
8.250 1.0548 0.03855 0.02749 -0.0295 0.1491 1.0000
8.500 1.0762 0.04100 0.03022 -0.0284 0.1408 1.0000
8.750 1.0954 0.04391 0.03337 -0.0272 0.1345 1.0000
9.000 1.1092 0.04716 0.03711 -0.0252 0.1310 1.0000
9.250 1.1238 0.05025 0.04045 -0.0237 0.1269 1.0000
9.500 1.1381 0.05396 0.04431 -0.0225 0.1230 1.0000
9.750 1.1379 0.05780 0.04868 -0.0198 0.1222 1.0000
10.000 1.1368 0.06207 0.05336 -0.0175 0.1223 1.0000
10.250 1.1310 0.06650 0.05815 -0.0151 0.1226 1.0000
10.500 1.1225 0.07102 0.06297 -0.0130 0.1231 1.0000
10.750 1.1124 0.07570 0.06787 -0.0112 0.1235 1.0000
11.000 1.0149 0.08155 0.07421 -0.0081 0.1302 1.0000
11.250 0.9752 0.08902 0.08176 -0.0107 0.1333 1.0000
11.500 0.9546 0.09642 0.08918 -0.0136 0.1358 1.0000
11.750 0.8630 0.12051 0.11308 -0.0327 0.1625 1.0000
12.000 0.8763 0.12541 0.11807 -0.0324 0.1654 1.0000
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Polar data table (+)
Polar graphs
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