GOE 445 AIRFOIL (goe445-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 445 AIRFOIL (goe445-il) Reynolds number: 100,000 Max Cl/Cd: 24.2 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe445-il-100000.txt Download as CSV file: xf-goe445-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 445 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6648 0.09061 0.08596 -0.0086 1.0000 0.0969
-8.250 -0.6797 0.08658 0.08189 -0.0126 1.0000 0.0973
-8.000 -0.6975 0.08336 0.07845 -0.0158 1.0000 0.0978
-7.750 -0.6732 0.07811 0.07344 -0.0126 1.0000 0.1097
-7.500 -0.6657 0.07369 0.06907 -0.0113 1.0000 0.1156
-7.250 -0.6811 0.07068 0.06572 -0.0153 1.0000 0.1238
-7.000 -0.6620 0.06600 0.06128 -0.0125 1.0000 0.1322
-6.750 -0.6580 0.06221 0.05743 -0.0125 1.0000 0.1437
-6.500 -0.6516 0.05884 0.05390 -0.0121 1.0000 0.1581
-5.500 -0.6143 0.04701 0.04197 -0.0062 1.0000 0.2504
-5.250 -0.5745 0.03482 0.02678 -0.0084 1.0000 0.0722
-5.000 -0.5491 0.03104 0.02253 -0.0064 1.0000 0.0572
-4.750 -0.5275 0.02748 0.01868 -0.0049 1.0000 0.0529
-4.500 -0.5031 0.02484 0.01552 -0.0031 1.0000 0.0493
-4.250 -0.4795 0.02310 0.01359 -0.0019 1.0000 0.0540
-4.000 -0.4542 0.02133 0.01155 -0.0005 1.0000 0.0563
-3.750 -0.4291 0.01959 0.00968 0.0009 1.0000 0.0575
-3.500 -0.4076 0.01775 0.00791 0.0025 1.0000 0.0608
-3.250 -0.3876 0.01651 0.00661 0.0044 1.0000 0.0684
-3.000 -0.3686 0.01524 0.00541 0.0062 1.0000 0.0930
-2.750 -0.2776 0.01278 0.00635 0.0015 1.0000 0.9580
-2.500 -0.1997 0.01270 0.00573 -0.0087 1.0000 0.9836
-2.250 -0.1380 0.01227 0.00489 -0.0166 1.0000 1.0000
-2.000 -0.1244 0.01190 0.00441 -0.0150 1.0000 1.0000
-1.750 -0.1100 0.01160 0.00402 -0.0134 1.0000 1.0000
-1.500 -0.0951 0.01138 0.00371 -0.0116 1.0000 1.0000
-1.250 -0.0799 0.01120 0.00346 -0.0097 1.0000 1.0000
-1.000 -0.0645 0.01106 0.00327 -0.0077 1.0000 1.0000
-0.750 -0.0488 0.01096 0.00311 -0.0058 1.0000 1.0000
-0.500 -0.0328 0.01089 0.00300 -0.0038 1.0000 1.0000
-0.250 -0.0164 0.01085 0.00294 -0.0019 1.0000 1.0000
0.000 0.0000 0.01083 0.00292 0.0000 1.0000 1.0000
0.250 0.0164 0.01085 0.00294 0.0019 1.0000 1.0000
0.500 0.0328 0.01089 0.00300 0.0038 1.0000 1.0000
0.750 0.0488 0.01096 0.00310 0.0058 1.0000 1.0000
1.000 0.0645 0.01106 0.00327 0.0077 1.0000 1.0000
1.250 0.0800 0.01120 0.00346 0.0097 1.0000 1.0000
1.500 0.0952 0.01137 0.00371 0.0115 1.0000 1.0000
1.750 0.1101 0.01160 0.00402 0.0133 1.0000 1.0000
2.000 0.1245 0.01189 0.00441 0.0150 1.0000 1.0000
2.250 0.1381 0.01226 0.00489 0.0166 1.0000 1.0000
2.500 0.1996 0.01269 0.00573 0.0087 0.9837 1.0000
2.750 0.2763 0.01279 0.00634 -0.0012 0.9584 1.0000
3.000 0.3685 0.01523 0.00540 -0.0062 0.0937 1.0000
3.250 0.3875 0.01651 0.00661 -0.0044 0.0687 1.0000
3.500 0.4075 0.01775 0.00792 -0.0025 0.0608 1.0000
3.750 0.4290 0.01959 0.00968 -0.0009 0.0575 1.0000
4.000 0.4541 0.02132 0.01154 0.0005 0.0564 1.0000
4.250 0.4795 0.02314 0.01362 0.0019 0.0544 1.0000
4.500 0.5032 0.02484 0.01556 0.0032 0.0500 1.0000
4.750 0.5274 0.02747 0.01867 0.0049 0.0529 1.0000
5.000 0.5491 0.03102 0.02252 0.0064 0.0572 1.0000
5.250 0.5745 0.03478 0.02675 0.0084 0.0723 1.0000
6.500 0.6518 0.05883 0.05389 0.0121 0.1582 1.0000
6.750 0.6581 0.06223 0.05744 0.0126 0.1433 1.0000
7.000 0.6620 0.06602 0.06130 0.0125 0.1320 1.0000
7.250 0.6806 0.07065 0.06570 0.0152 0.1237 1.0000
8.250 0.6023 0.07863 0.07429 0.0133 0.1105 1.0000
8.500 0.5804 0.08336 0.07898 0.0091 0.1103 1.0000
8.750 0.5587 0.08808 0.08362 0.0039 0.1093 1.0000
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Polar data table (+)
Polar graphs
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