GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 9K AIRFOIL (goe09k-il) Reynolds number: 200,000 Max Cl/Cd: 29.11 at α=1.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe09k-il-200000-n5.txt Download as CSV file: xf-goe09k-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5875 0.10039 0.09682 0.0051 1.0000 0.0101
-8.000 -0.5851 0.09716 0.09363 0.0030 1.0000 0.0101
-7.750 -0.5837 0.09384 0.09036 0.0007 1.0000 0.0101
-7.500 -0.5788 0.09017 0.08672 -0.0026 1.0000 0.0102
-7.250 -0.5765 0.08584 0.08242 -0.0018 1.0000 0.0105
-7.000 -0.5707 0.08204 0.07863 -0.0036 1.0000 0.0108
-6.750 -0.5623 0.07805 0.07464 -0.0066 1.0000 0.0111
-6.500 -0.5516 0.07401 0.07059 -0.0098 1.0000 0.0116
-6.250 -0.5386 0.06972 0.06626 -0.0133 1.0000 0.0121
-6.000 -0.5231 0.06545 0.06193 -0.0168 1.0000 0.0126
-5.750 -0.5021 0.06097 0.05735 -0.0207 1.0000 0.0135
-5.500 -0.4752 0.05685 0.05302 -0.0243 1.0000 0.0140
-5.250 -0.4518 0.05293 0.04889 -0.0262 1.0000 0.0142
-5.000 -0.4436 0.04774 0.04367 -0.0268 1.0000 0.0150
-4.750 -0.4259 0.04415 0.03995 -0.0274 1.0000 0.0161
-4.500 -0.4038 0.04060 0.03619 -0.0280 1.0000 0.0174
-4.250 -0.3719 0.03892 0.03411 -0.0276 1.0000 0.0203
-4.000 -0.3517 0.03407 0.02892 -0.0277 1.0000 0.0212
-3.750 -0.3332 0.03011 0.02480 -0.0277 1.0000 0.0228
-3.250 -0.2818 0.02339 0.01728 -0.0253 1.0000 0.0094
-3.000 -0.2569 0.02068 0.01417 -0.0242 1.0000 0.0085
-2.750 -0.2314 0.01840 0.01147 -0.0231 1.0000 0.0085
-2.500 -0.2056 0.01639 0.00905 -0.0219 1.0000 0.0087
-2.250 -0.1797 0.01448 0.00678 -0.0207 1.0000 0.0081
-2.000 -0.1546 0.01296 0.00502 -0.0195 1.0000 0.0081
-1.750 -0.1302 0.01180 0.00374 -0.0185 1.0000 0.0089
-1.500 -0.1058 0.01095 0.00280 -0.0177 1.0000 0.0125
-1.250 -0.0809 0.01027 0.00194 -0.0168 1.0000 0.0212
-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 0.2160 0.00742 0.00187 -0.0168 0.9918 1.0000
1.750 0.3076 0.01099 0.00226 -0.0298 0.0156 1.0000
2.000 0.3315 0.01183 0.00326 -0.0288 0.0104 1.0000
2.250 0.3552 0.01276 0.00435 -0.0276 0.0085 1.0000
2.500 0.3785 0.01409 0.00578 -0.0263 0.0080 1.0000
2.750 0.4024 0.01593 0.00770 -0.0252 0.0074 1.0000
3.000 0.4289 0.01743 0.00956 -0.0240 0.0069 1.0000
3.250 0.4548 0.01955 0.01205 -0.0227 0.0069 1.0000
3.500 0.4810 0.02203 0.01499 -0.0212 0.0084 1.0000
3.750 0.5064 0.02529 0.01870 -0.0194 0.0129 1.0000
6.000 0.6828 0.05917 0.05529 -0.0126 0.0138 1.0000
6.250 0.7005 0.06358 0.05990 -0.0139 0.0129 1.0000
6.500 0.7133 0.06815 0.06460 -0.0155 0.0123 1.0000
6.750 0.7235 0.07276 0.06931 -0.0175 0.0117 1.0000
7.000 0.7309 0.07733 0.07394 -0.0196 0.0113 1.0000
7.250 0.7360 0.08169 0.07834 -0.0215 0.0109 1.0000
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Polar data table (+)
Polar graphs
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