GOE 10K AIRFOIL (goe10k-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 10K AIRFOIL (goe10k-il) Reynolds number: 200,000 Max Cl/Cd: 56.41 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe10k-il-200000-n5.txt Download as CSV file: xf-goe10k-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 10K 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5331 0.09244 0.08893 -0.0124 1.0000 0.0131
-7.750 -0.5325 0.08931 0.08582 -0.0122 1.0000 0.0135
-7.500 -0.5347 0.08631 0.08287 -0.0130 1.0000 0.0135
-7.250 -0.5323 0.08305 0.07965 -0.0139 1.0000 0.0143
-7.000 -0.5285 0.07933 0.07594 -0.0164 1.0000 0.0142
-6.750 -0.5221 0.07571 0.07233 -0.0189 1.0000 0.0155
-6.500 -0.5144 0.07171 0.06832 -0.0215 1.0000 0.0156
-6.000 -0.4759 0.06408 0.06046 -0.0296 1.0000 0.0178
-5.500 -0.4632 0.05394 0.05019 -0.0310 1.0000 0.0190
-5.250 -0.4527 0.05062 0.04682 -0.0307 1.0000 0.0203
-5.000 -0.4373 0.04704 0.04310 -0.0310 1.0000 0.0212
-4.750 -0.4201 0.04332 0.03919 -0.0312 1.0000 0.0224
-4.500 -0.4015 0.03957 0.03521 -0.0310 1.0000 0.0229
-4.250 -0.3766 0.03302 0.02812 -0.0298 1.0000 0.0133
-4.000 -0.3582 0.02979 0.02462 -0.0288 1.0000 0.0107
-3.750 -0.3347 0.02509 0.01932 -0.0270 1.0000 0.0090
-3.500 -0.3130 0.02219 0.01598 -0.0257 1.0000 0.0087
-3.250 -0.2897 0.01952 0.01279 -0.0244 1.0000 0.0085
-3.000 -0.2650 0.01737 0.01009 -0.0230 1.0000 0.0091
-2.750 -0.2416 0.01592 0.00841 -0.0221 1.0000 0.0105
-2.500 -0.2169 0.01446 0.00668 -0.0210 1.0000 0.0112
-2.250 -0.1930 0.01338 0.00541 -0.0199 1.0000 0.0123
-2.000 -0.1698 0.01259 0.00454 -0.0189 1.0000 0.0160
-1.750 -0.1464 0.01189 0.00368 -0.0179 1.0000 0.0208
-1.500 -0.1167 0.01128 0.00317 -0.0183 0.9981 0.0636
-1.250 -0.0878 0.01058 0.00298 -0.0192 0.9960 0.1964
-1.000 -0.0652 0.00925 0.00293 -0.0188 0.9938 0.5695
-0.750 -0.0162 0.00825 0.00281 -0.0229 0.9989 1.0000
-0.500 0.0171 0.00836 0.00273 -0.0243 0.9960 1.0000
-0.250 0.0493 0.00845 0.00271 -0.0255 0.9930 1.0000
0.000 0.0818 0.00855 0.00271 -0.0268 0.9898 1.0000
0.250 0.1157 0.00867 0.00278 -0.0283 0.9870 1.0000
0.500 0.1484 0.00872 0.00281 -0.0296 0.9820 1.0000
0.750 0.1890 0.00873 0.00283 -0.0325 0.9751 1.0000
1.000 0.2318 0.00868 0.00283 -0.0358 0.9670 1.0000
1.250 0.2702 0.00856 0.00278 -0.0380 0.9557 1.0000
1.500 0.3101 0.00837 0.00272 -0.0403 0.9417 1.0000
1.750 0.3596 0.00801 0.00252 -0.0444 0.9148 1.0000
2.000 0.4310 0.00764 0.00228 -0.0529 0.8295 1.0000
2.250 0.4476 0.00936 0.00229 -0.0496 0.4197 1.0000
2.500 0.4544 0.01144 0.00283 -0.0462 0.0843 1.0000
2.750 0.4750 0.01229 0.00343 -0.0447 0.0221 1.0000
3.000 0.4970 0.01303 0.00430 -0.0433 0.0149 1.0000
3.250 0.5181 0.01403 0.00543 -0.0417 0.0124 1.0000
3.500 0.5397 0.01504 0.00653 -0.0403 0.0106 1.0000
3.750 0.5616 0.01640 0.00803 -0.0388 0.0090 1.0000
4.000 0.5853 0.01812 0.00998 -0.0374 0.0086 1.0000
4.250 0.6100 0.02031 0.01252 -0.0360 0.0084 1.0000
4.500 0.6339 0.02290 0.01555 -0.0343 0.0084 1.0000
4.750 0.6553 0.02492 0.01791 -0.0329 0.0074 1.0000
5.000 0.6746 0.02788 0.02131 -0.0310 0.0069 1.0000
5.500 0.7106 0.03646 0.03096 -0.0252 0.0086 1.0000
5.750 0.7243 0.03966 0.03441 -0.0235 0.0101 1.0000
6.250 0.7429 0.05147 0.04682 -0.0189 0.0194 1.0000
6.500 0.7449 0.05763 0.05323 -0.0175 0.0189 1.0000
6.750 0.7540 0.06137 0.05722 -0.0162 0.0188 1.0000
7.000 0.7694 0.06397 0.06011 -0.0153 0.0180 1.0000
7.250 0.7780 0.06824 0.06459 -0.0152 0.0169 1.0000
7.500 0.7813 0.07261 0.06909 -0.0155 0.0165 1.0000
7.750 0.7815 0.07719 0.07375 -0.0164 0.0162 1.0000
8.000 0.7793 0.08169 0.07831 -0.0177 0.0160 1.0000
8.250 0.7727 0.08584 0.08248 -0.0188 0.0159 1.0000
8.500 0.7654 0.09044 0.08709 -0.0219 0.0159 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 10K AIRFOIL (goe10k-il)