GOE 9K AIRFOIL (goe09k-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 9K AIRFOIL (goe09k-il) Reynolds number: 100,000 Max Cl/Cd: 23.83 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe09k-il-100000-n5.txt Download as CSV file: xf-goe09k-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5890 0.09910 0.09416 0.0055 1.0000 0.0295
-7.750 -0.5882 0.09605 0.09117 0.0029 1.0000 0.0307
-7.500 -0.5858 0.09282 0.08801 -0.0003 1.0000 0.0311
-7.250 -0.5786 0.08914 0.08435 -0.0051 1.0000 0.0314
-7.000 -0.5682 0.08525 0.08045 -0.0105 1.0000 0.0316
-6.750 -0.5548 0.08118 0.07631 -0.0156 1.0000 0.0317
-6.500 -0.5548 0.07661 0.07186 -0.0104 1.0000 0.0345
-6.250 -0.5411 0.07251 0.06771 -0.0143 1.0000 0.0376
-6.000 -0.5171 0.06853 0.06350 -0.0218 1.0000 0.0391
-5.750 -0.5114 0.06384 0.05890 -0.0203 1.0000 0.0415
-5.500 -0.4923 0.06006 0.05496 -0.0230 1.0000 0.0457
-5.250 -0.4712 0.05561 0.05028 -0.0261 1.0000 0.0488
-5.000 -0.4571 0.05171 0.04636 -0.0261 1.0000 0.0520
-4.500 -0.4142 0.04413 0.03832 -0.0285 1.0000 0.0620
-4.250 -0.3912 0.04061 0.03449 -0.0293 1.0000 0.0693
-4.000 -0.3682 0.03736 0.03097 -0.0293 1.0000 0.0728
-3.750 -0.3350 0.03214 0.02520 -0.0281 1.0000 0.0245
-3.500 -0.3074 0.02908 0.02161 -0.0271 1.0000 0.0186
-3.250 -0.2824 0.02593 0.01801 -0.0263 1.0000 0.0165
-3.000 -0.2549 0.02326 0.01470 -0.0250 1.0000 0.0146
-2.750 -0.2288 0.02129 0.01227 -0.0239 1.0000 0.0141
-2.500 -0.2039 0.01893 0.00963 -0.0231 1.0000 0.0157
-2.250 -0.1783 0.01721 0.00767 -0.0220 1.0000 0.0173
-2.000 -0.1536 0.01565 0.00589 -0.0209 1.0000 0.0183
-1.750 -0.1298 0.01433 0.00439 -0.0197 1.0000 0.0227
-1.500 -0.1052 0.01339 0.00326 -0.0187 1.0000 0.0324
-1.250 -0.0608 0.00956 0.00231 -0.0219 1.0000 1.0000
-1.000 -0.0369 0.00955 0.00185 -0.0210 1.0000 1.0000
-0.750 -0.0129 0.00955 0.00158 -0.0202 1.0000 1.0000
-0.500 0.0109 0.00956 0.00140 -0.0194 1.0000 1.0000
-0.250 0.0347 0.00959 0.00128 -0.0187 1.0000 1.0000
0.000 0.0585 0.00962 0.00121 -0.0180 1.0000 1.0000
0.250 0.0822 0.00967 0.00121 -0.0173 1.0000 1.0000
0.500 0.1059 0.00972 0.00127 -0.0165 1.0000 1.0000
0.750 0.1294 0.00979 0.00139 -0.0158 1.0000 1.0000
1.000 0.1530 0.00987 0.00156 -0.0151 1.0000 1.0000
1.250 0.1764 0.00996 0.00178 -0.0143 1.0000 1.0000
1.500 0.1998 0.01007 0.00207 -0.0136 1.0000 1.0000
1.750 0.2232 0.01019 0.00253 -0.0128 1.0000 1.0000
2.000 0.2464 0.01034 0.00304 -0.0120 1.0000 1.0000
2.250 0.3534 0.01530 0.00500 -0.0264 0.0198 1.0000
2.500 0.3765 0.01659 0.00649 -0.0250 0.0177 1.0000
2.750 0.4001 0.01825 0.00821 -0.0238 0.0151 1.0000
3.000 0.4256 0.02024 0.01041 -0.0227 0.0139 1.0000
3.250 0.4520 0.02257 0.01305 -0.0216 0.0141 1.0000
3.500 0.4777 0.02510 0.01598 -0.0205 0.0147 1.0000
3.750 0.5054 0.02745 0.01898 -0.0187 0.0168 1.0000
4.000 0.5294 0.03073 0.02273 -0.0173 0.0191 1.0000
4.250 0.5560 0.03378 0.02632 -0.0155 0.0252 1.0000
5.750 0.6762 0.05826 0.05266 -0.0111 0.0489 1.0000
6.250 0.7049 0.06617 0.06111 -0.0127 0.0409 1.0000
6.500 0.7122 0.07175 0.06663 -0.0125 0.0395 1.0000
6.750 0.7263 0.07544 0.07069 -0.0169 0.0373 1.0000
7.000 0.7342 0.07991 0.07525 -0.0193 0.0352 1.0000
7.250 0.7400 0.08417 0.07953 -0.0205 0.0335 1.0000
7.500 0.7434 0.08947 0.08475 -0.0181 0.0322 1.0000
7.750 0.7477 0.09375 0.08910 -0.0215 0.0321 1.0000
8.000 0.7492 0.09804 0.09341 -0.0256 0.0319 1.0000
8.250 0.7475 0.10210 0.09743 -0.0294 0.0318 1.0000
8.500 0.7464 0.10603 0.10131 -0.0330 0.0317 1.0000
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Polar data table (+)
Polar graphs
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