GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 280 (DAIMLER XI) AIRFOIL (goe280-il) Reynolds number: 500,000 Max Cl/Cd: 91.58 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe280-il-500000.txt Download as CSV file: xf-goe280-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 280 (DAIMLER XI) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
0.750 0.5479 0.01052 0.00346 -0.0822 0.5960 0.0461
1.000 0.5754 0.01038 0.00318 -0.0821 0.5657 0.0460
1.250 0.6032 0.01031 0.00299 -0.0821 0.5416 0.0462
1.500 0.6309 0.01031 0.00288 -0.0821 0.5212 0.0473
1.750 0.6589 0.01031 0.00280 -0.0822 0.5027 0.0480
2.000 0.6869 0.01031 0.00272 -0.0823 0.4858 0.0480
2.250 0.7148 0.01035 0.00269 -0.0823 0.4687 0.0485
2.500 0.7425 0.01044 0.00268 -0.0824 0.4487 0.0496
2.750 0.7702 0.01054 0.00267 -0.0824 0.4266 0.0564
3.000 0.7907 0.00876 0.00284 -0.0813 0.4074 1.0000
3.250 0.8182 0.00897 0.00293 -0.0813 0.3859 1.0000
3.500 0.8453 0.00923 0.00304 -0.0813 0.3636 1.0000
3.750 0.8721 0.00953 0.00319 -0.0812 0.3357 1.0000
4.000 0.8979 0.00997 0.00339 -0.0811 0.2942 1.0000
4.250 0.9233 0.01048 0.00366 -0.0810 0.2508 1.0000
4.500 0.9490 0.01094 0.00392 -0.0808 0.2179 1.0000
4.750 0.9741 0.01148 0.00423 -0.0806 0.1825 1.0000
5.000 0.9994 0.01196 0.00453 -0.0805 0.1548 1.0000
5.250 1.0250 0.01238 0.00484 -0.0803 0.1355 1.0000
5.500 1.0504 0.01281 0.00514 -0.0802 0.1187 1.0000
5.750 1.0747 0.01338 0.00550 -0.0799 0.0901 1.0000
6.000 1.0958 0.01443 0.00621 -0.0791 0.0389 1.0000
6.250 1.1194 0.01509 0.00672 -0.0786 0.0181 1.0000
6.500 1.1449 0.01543 0.00715 -0.0783 0.0163 1.0000
6.750 1.1696 0.01589 0.00772 -0.0778 0.0151 1.0000
7.000 1.1937 0.01641 0.00835 -0.0773 0.0143 1.0000
7.250 1.2171 0.01703 0.00908 -0.0767 0.0137 1.0000
7.500 1.2395 0.01775 0.00994 -0.0759 0.0132 1.0000
7.750 1.2608 0.01858 0.01089 -0.0749 0.0128 1.0000
8.000 1.2786 0.01978 0.01223 -0.0735 0.0124 1.0000
8.250 1.2972 0.02077 0.01331 -0.0723 0.0118 1.0000
8.500 1.3154 0.02172 0.01435 -0.0709 0.0116 1.0000
8.750 1.3315 0.02282 0.01555 -0.0693 0.0115 1.0000
9.000 1.3454 0.02403 0.01685 -0.0673 0.0114 1.0000
9.250 1.3564 0.02541 0.01831 -0.0649 0.0115 1.0000
9.500 1.3619 0.02714 0.02011 -0.0618 0.0117 1.0000
9.750 1.2715 0.01642 0.00983 -0.0455 0.0123 1.0000
10.750 1.3499 0.01702 0.01103 -0.0407 0.0199 1.0000
11.000 1.3436 0.01927 0.01341 -0.0376 0.0196 1.0000
11.250 1.3339 0.02219 0.01643 -0.0347 0.0190 1.0000
11.500 1.3264 0.02533 0.01967 -0.0323 0.0186 1.0000
11.750 1.3184 0.02892 0.02334 -0.0301 0.0182 1.0000
12.000 1.3133 0.03286 0.02731 -0.0280 0.0176 1.0000
12.250 1.3000 0.03802 0.03266 -0.0259 0.0162 1.0000
12.500 1.2940 0.04162 0.03641 -0.0250 0.0158 1.0000
12.750 1.2878 0.04556 0.04049 -0.0241 0.0154 1.0000
13.000 1.2810 0.04972 0.04478 -0.0233 0.0150 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 280 (DAIMLER XI) AIRFOIL (goe280-il)