GOE 5K AIRFOIL (goe05k-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 5K AIRFOIL (goe05k-il) Reynolds number: 200,000 Max Cl/Cd: 33.45 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe05k-il-200000.txt Download as CSV file: xf-goe05k-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 5K 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.5200 0.09207 0.08857 -0.0115 1.0000 0.0159
-7.500 -0.5208 0.08928 0.08582 -0.0122 1.0000 0.0161
-7.250 -0.5193 0.08618 0.08276 -0.0139 1.0000 0.0165
-7.000 -0.5132 0.08289 0.07950 -0.0171 1.0000 0.0170
-6.750 -0.5035 0.07947 0.07608 -0.0212 1.0000 0.0174
-6.500 -0.4897 0.07610 0.07267 -0.0254 1.0000 0.0177
-6.250 -0.4744 0.07276 0.06925 -0.0287 1.0000 0.0179
-6.000 -0.4593 0.06938 0.06578 -0.0307 1.0000 0.0181
-5.750 -0.4527 0.06383 0.06020 -0.0319 1.0000 0.0185
-5.500 -0.4521 0.05909 0.05551 -0.0306 1.0000 0.0196
-5.250 -0.4416 0.05548 0.05184 -0.0307 1.0000 0.0209
-5.000 -0.4266 0.05189 0.04815 -0.0314 1.0000 0.0223
-4.750 -0.4091 0.04835 0.04445 -0.0321 1.0000 0.0240
-4.500 -0.3889 0.04482 0.04072 -0.0327 1.0000 0.0262
-4.250 -0.3581 0.04314 0.03849 -0.0327 1.0000 0.0283
-4.000 -0.3461 0.03795 0.03330 -0.0325 1.0000 0.0295
-3.750 -0.3301 0.03498 0.03024 -0.0320 1.0000 0.0331
-3.500 -0.3068 0.03215 0.02700 -0.0312 1.0000 0.0381
-3.250 -0.2858 0.02981 0.02435 -0.0303 1.0000 0.0463
-3.000 -0.2640 0.02812 0.02225 -0.0293 1.0000 0.0571
-2.750 -0.2436 0.02527 0.01923 -0.0287 1.0000 0.0703
-2.500 -0.2228 0.02277 0.01664 -0.0281 1.0000 0.0871
-1.750 -0.1363 0.01653 0.00899 -0.0232 1.0000 0.0350
-1.500 -0.1085 0.01486 0.00705 -0.0219 1.0000 0.0269
-1.250 -0.0831 0.01364 0.00568 -0.0209 1.0000 0.0274
-1.000 -0.0585 0.01240 0.00438 -0.0198 1.0000 0.0277
-0.750 -0.0349 0.01155 0.00349 -0.0188 1.0000 0.0369
-0.500 0.0155 0.00819 0.00272 -0.0235 1.0000 1.0000
-0.250 0.0379 0.00829 0.00261 -0.0226 1.0000 1.0000
0.000 0.0601 0.00841 0.00258 -0.0217 1.0000 1.0000
0.250 0.0824 0.00854 0.00261 -0.0209 1.0000 1.0000
0.500 0.1045 0.00868 0.00267 -0.0201 1.0000 1.0000
0.750 0.1267 0.00883 0.00278 -0.0193 1.0000 1.0000
1.000 0.1486 0.00901 0.00295 -0.0185 1.0000 1.0000
1.250 0.1705 0.00920 0.00316 -0.0178 1.0000 1.0000
1.500 0.1920 0.00941 0.00341 -0.0170 1.0000 1.0000
1.750 0.2137 0.00964 0.00371 -0.0163 1.0000 1.0000
2.000 0.2350 0.00989 0.00407 -0.0155 1.0000 1.0000
2.250 0.2981 0.01025 0.00479 -0.0234 0.9882 1.0000
2.500 0.4499 0.01345 0.00490 -0.0441 0.0222 1.0000
2.750 0.4716 0.01488 0.00641 -0.0422 0.0232 1.0000
3.000 0.4974 0.01688 0.00851 -0.0406 0.0270 1.0000
3.250 0.5266 0.01909 0.01096 -0.0393 0.0347 1.0000
5.250 0.7032 0.04163 0.03644 -0.0244 0.0350 1.0000
5.500 0.7162 0.04537 0.04021 -0.0235 0.0312 1.0000
5.750 0.7280 0.04972 0.04491 -0.0217 0.0298 1.0000
6.000 0.7460 0.05270 0.04834 -0.0199 0.0266 1.0000
6.250 0.7576 0.05663 0.05249 -0.0190 0.0244 1.0000
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Polar data table (+)
Polar graphs
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