GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il) Reynolds number: 500,000 Max Cl/Cd: 88.15 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe100-il-500000.txt Download as CSV file: xf-goe100-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 100 (SOPWITH) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3935 0.09358 0.09143 -0.0217 1.0000 0.0129
-7.750 -0.3954 0.09075 0.08864 -0.0219 1.0000 0.0129
-6.500 -0.4171 0.07305 0.07111 -0.0242 1.0000 0.0136
-6.250 -0.4048 0.06969 0.06773 -0.0263 0.9987 0.0142
-6.000 -0.3787 0.06587 0.06387 -0.0312 0.9964 0.0150
-5.750 -0.3483 0.06172 0.05965 -0.0373 0.9944 0.0170
-5.500 -0.3134 0.05634 0.05416 -0.0445 0.9909 0.0195
-5.250 -0.2698 0.05169 0.04935 -0.0512 0.9879 0.0208
-5.000 -0.2340 0.04625 0.04372 -0.0564 0.9855 0.0210
-4.750 -0.2066 0.03798 0.03521 -0.0624 0.9834 0.0226
-4.500 -0.1773 0.03533 0.03244 -0.0646 0.9801 0.0239
-4.250 -0.1443 0.03181 0.02872 -0.0671 0.9764 0.0261
-4.000 -0.1064 0.01659 0.01181 -0.0685 0.9740 0.0135
-3.750 -0.0709 0.01350 0.00815 -0.0699 0.9724 0.0141
-3.500 -0.0340 0.01201 0.00641 -0.0717 0.9709 0.0156
-3.250 0.0033 0.01131 0.00562 -0.0736 0.9689 0.0180
-3.000 0.0350 0.01046 0.00464 -0.0741 0.9625 0.0197
-2.750 0.0712 0.00950 0.00353 -0.0755 0.9577 0.0237
-2.500 0.1016 0.00907 0.00317 -0.0757 0.9495 0.0379
-2.250 0.1340 0.00899 0.00306 -0.0765 0.9437 0.0554
-2.000 0.1620 0.00869 0.00275 -0.0764 0.9350 0.0633
-1.750 0.1913 0.00853 0.00251 -0.0765 0.9268 0.0691
-1.500 0.2193 0.00828 0.00225 -0.0763 0.9163 0.0781
-1.250 0.2462 0.00814 0.00205 -0.0759 0.9041 0.0830
-1.000 0.2732 0.00795 0.00190 -0.0755 0.8929 0.0968
-0.750 0.3001 0.00776 0.00186 -0.0752 0.8821 0.1570
-0.500 0.3271 0.00766 0.00179 -0.0749 0.8709 0.1879
-0.250 0.3540 0.00756 0.00172 -0.0746 0.8590 0.2132
0.000 0.3806 0.00737 0.00168 -0.0743 0.8459 0.2712
0.250 0.3960 0.00574 0.00175 -0.0718 0.8319 0.8662
0.500 0.4390 0.00558 0.00167 -0.0745 0.8137 1.0000
0.750 0.4644 0.00564 0.00161 -0.0738 0.7926 1.0000
1.000 0.4898 0.00572 0.00157 -0.0731 0.7664 1.0000
1.250 0.5148 0.00584 0.00154 -0.0724 0.7303 1.0000
1.500 0.5381 0.00611 0.00152 -0.0712 0.6693 1.0000
1.750 0.5598 0.00658 0.00159 -0.0699 0.5876 1.0000
2.000 0.5828 0.00704 0.00171 -0.0690 0.5237 1.0000
2.250 0.6070 0.00741 0.00185 -0.0684 0.4751 1.0000
2.500 0.6317 0.00776 0.00199 -0.0678 0.4284 1.0000
2.750 0.6548 0.00831 0.00219 -0.0671 0.3574 1.0000
3.000 0.6782 0.00885 0.00238 -0.0665 0.2951 1.0000
3.250 0.7030 0.00924 0.00256 -0.0661 0.2559 1.0000
3.500 0.7278 0.00963 0.00274 -0.0657 0.2166 1.0000
3.750 0.7523 0.01008 0.00297 -0.0653 0.1763 1.0000
4.000 0.7766 0.01056 0.00322 -0.0648 0.1377 1.0000
4.250 0.7955 0.01188 0.00389 -0.0636 0.0259 1.0000
4.500 0.8216 0.01214 0.00421 -0.0632 0.0191 1.0000
4.750 0.8473 0.01248 0.00464 -0.0628 0.0173 1.0000
5.000 0.8724 0.01292 0.00520 -0.0622 0.0152 1.0000
5.250 0.8970 0.01347 0.00591 -0.0615 0.0141 1.0000
5.500 0.9205 0.01420 0.00678 -0.0606 0.0136 1.0000
5.750 0.9439 0.01491 0.00757 -0.0598 0.0137 1.0000
6.000 0.9679 0.01550 0.00822 -0.0590 0.0145 1.0000
6.250 0.9932 0.01591 0.00873 -0.0582 0.0164 1.0000
6.500 1.0129 0.01705 0.00998 -0.0568 0.0152 1.0000
6.750 1.0361 0.01776 0.01083 -0.0556 0.0172 1.0000
7.000 1.0559 0.01899 0.01215 -0.0538 0.0189 1.0000
7.250 1.0752 0.02037 0.01361 -0.0522 0.0184 1.0000
7.500 1.0946 0.02185 0.01516 -0.0507 0.0170 1.0000
7.750 1.1139 0.02365 0.01699 -0.0494 0.0156 1.0000
8.000 1.1343 0.02599 0.01930 -0.0484 0.0144 1.0000
8.250 1.1570 0.03302 0.02639 -0.0483 0.0127 1.0000
8.500 1.1747 0.03492 0.02853 -0.0467 0.0126 1.0000
8.750 1.1896 0.03619 0.03010 -0.0447 0.0125 1.0000
9.000 1.2047 0.03564 0.02979 -0.0425 0.0117 1.0000
9.250 1.2197 0.03686 0.03123 -0.0406 0.0109 1.0000
9.500 1.2323 0.03871 0.03330 -0.0385 0.0104 1.0000
9.750 1.2420 0.04088 0.03569 -0.0363 0.0099 1.0000
10.000 1.2484 0.04325 0.03829 -0.0338 0.0095 1.0000
10.250 1.2514 0.04577 0.04103 -0.0311 0.0093 1.0000
10.500 1.2509 0.04837 0.04384 -0.0282 0.0090 1.0000
10.750 1.2450 0.05091 0.04658 -0.0247 0.0089 1.0000
11.000 1.2347 0.05344 0.04929 -0.0210 0.0088 1.0000
11.250 1.2227 0.05626 0.05227 -0.0180 0.0087 1.0000
11.500 1.2096 0.05942 0.05560 -0.0159 0.0086 1.0000
11.750 1.1954 0.06300 0.05935 -0.0148 0.0085 1.0000
12.000 1.1803 0.06706 0.06357 -0.0146 0.0084 1.0000
12.250 1.1640 0.07168 0.06836 -0.0155 0.0084 1.0000
12.500 1.1469 0.07704 0.07388 -0.0177 0.0084 1.0000
12.750 1.1293 0.08321 0.08022 -0.0213 0.0085 1.0000
13.000 1.1110 0.09042 0.08759 -0.0262 0.0085 1.0000
13.250 1.0921 0.09861 0.09594 -0.0322 0.0086 1.0000
13.500 1.0725 0.10779 0.10528 -0.0388 0.0088 1.0000
13.750 1.0526 0.11778 0.11541 -0.0458 0.0090 1.0000
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Polar data table (+)
Polar graphs
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