GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 9K AIRFOIL (goe09k-il) Reynolds number: 200,000 Max Cl/Cd: 29.31 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe09k-il-200000.txt Download as CSV file: xf-goe09k-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 9K 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5855 0.09677 0.09323 0.0055 1.0000 0.0167
-7.750 -0.5833 0.09339 0.08990 0.0040 1.0000 0.0173
-7.500 -0.5819 0.09019 0.08674 0.0025 1.0000 0.0178
-7.250 -0.5775 0.08672 0.08329 -0.0002 1.0000 0.0183
-7.000 -0.5694 0.08298 0.07957 -0.0040 1.0000 0.0188
-6.750 -0.5567 0.07909 0.07568 -0.0090 1.0000 0.0195
-6.500 -0.5381 0.07537 0.07189 -0.0149 1.0000 0.0200
-6.250 -0.5176 0.07174 0.06815 -0.0195 1.0000 0.0204
-6.000 -0.4994 0.06797 0.06426 -0.0222 1.0000 0.0205
-5.750 -0.4988 0.06085 0.05720 -0.0229 1.0000 0.0217
-5.500 -0.4889 0.05699 0.05332 -0.0230 1.0000 0.0232
-5.250 -0.4719 0.05307 0.04928 -0.0245 1.0000 0.0252
-5.000 -0.4516 0.04908 0.04513 -0.0262 1.0000 0.0275
-4.750 -0.4253 0.04522 0.04099 -0.0279 1.0000 0.0308
-4.500 -0.3987 0.04141 0.03675 -0.0289 1.0000 0.0321
-4.250 -0.3844 0.03771 0.03310 -0.0288 1.0000 0.0358
-4.000 -0.3599 0.03432 0.02935 -0.0288 1.0000 0.0408
-3.750 -0.3354 0.03182 0.02640 -0.0284 1.0000 0.0487
-3.500 -0.3128 0.02936 0.02359 -0.0279 1.0000 0.0589
-3.250 -0.2930 0.02618 0.02044 -0.0276 1.0000 0.0708
-3.000 -0.2707 0.02395 0.01801 -0.0270 1.0000 0.0911
-2.250 -0.1827 0.01589 0.00834 -0.0217 1.0000 0.0299
-2.000 -0.1562 0.01378 0.00595 -0.0203 1.0000 0.0242
-1.750 -0.1309 0.01230 0.00434 -0.0191 1.0000 0.0227
-1.500 -0.1065 0.01114 0.00315 -0.0181 1.0000 0.0277
-1.250 -0.0614 0.00688 0.00190 -0.0215 1.0000 1.0000
-1.000 -0.0374 0.00689 0.00151 -0.0206 1.0000 1.0000
-0.750 -0.0135 0.00690 0.00130 -0.0198 1.0000 1.0000
-0.500 0.0103 0.00692 0.00118 -0.0190 1.0000 1.0000
-0.250 0.0341 0.00695 0.00111 -0.0183 1.0000 1.0000
0.000 0.0579 0.00698 0.00106 -0.0175 1.0000 1.0000
0.250 0.0815 0.00703 0.00108 -0.0168 1.0000 1.0000
0.500 0.1051 0.00709 0.00114 -0.0160 1.0000 1.0000
0.750 0.1285 0.00716 0.00125 -0.0152 1.0000 1.0000
1.000 0.1519 0.00724 0.00139 -0.0145 1.0000 1.0000
1.250 0.1751 0.00733 0.00157 -0.0137 1.0000 1.0000
1.500 0.1983 0.00743 0.00182 -0.0129 1.0000 1.0000
1.750 0.2213 0.00755 0.00219 -0.0121 1.0000 1.0000
2.000 0.3323 0.01188 0.00350 -0.0283 0.0240 1.0000
2.250 0.3543 0.01348 0.00513 -0.0267 0.0219 1.0000
2.500 0.3798 0.01486 0.00665 -0.0253 0.0239 1.0000
2.750 0.4071 0.01711 0.00909 -0.0239 0.0303 1.0000
3.750 0.5192 0.02831 0.02187 -0.0171 0.0778 1.0000
4.000 0.5407 0.03032 0.02430 -0.0159 0.0608 1.0000
4.250 0.5615 0.03314 0.02744 -0.0149 0.0505 1.0000
4.500 0.5824 0.03611 0.03078 -0.0138 0.0426 1.0000
4.750 0.6020 0.03959 0.03457 -0.0129 0.0373 1.0000
5.000 0.6178 0.04334 0.03836 -0.0125 0.0328 1.0000
5.250 0.6390 0.04713 0.04264 -0.0117 0.0308 1.0000
5.500 0.6591 0.05105 0.04689 -0.0116 0.0274 1.0000
5.750 0.6750 0.05514 0.05118 -0.0119 0.0248 1.0000
6.000 0.6860 0.05925 0.05537 -0.0119 0.0227 1.0000
7.250 0.7352 0.08305 0.07971 -0.0218 0.0194 1.0000
7.500 0.7404 0.08742 0.08411 -0.0252 0.0190 1.0000
7.750 0.7417 0.09163 0.08832 -0.0285 0.0187 1.0000
8.000 0.7395 0.09572 0.09237 -0.0316 0.0184 1.0000
8.250 0.7393 0.09975 0.09637 -0.0341 0.0180 1.0000
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Polar data table (+)
Polar graphs
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