GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 397 AIRFOIL (goe397-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.94 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe397-il-1000000.txt Download as CSV file: xf-goe397-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 397 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4009 0.08969 0.08811 -0.0186 1.0000 0.0101
-7.750 -0.4006 0.08686 0.08530 -0.0191 1.0000 0.0101
-7.500 -0.4042 0.08225 0.08072 -0.0203 1.0000 0.0104
-7.250 -0.3969 0.07988 0.07836 -0.0209 1.0000 0.0106
-7.000 -0.3889 0.07732 0.07581 -0.0224 1.0000 0.0109
-6.750 -0.3801 0.07486 0.07336 -0.0239 1.0000 0.0113
-6.500 -0.3717 0.07170 0.07021 -0.0260 1.0000 0.0115
-6.250 -0.3563 0.06846 0.06696 -0.0292 0.9994 0.0128
-6.000 -0.3114 0.06235 0.06077 -0.0416 0.9938 0.0140
-5.750 -0.2792 0.05717 0.05553 -0.0486 0.9868 0.0141
-5.500 -0.2436 0.05128 0.04955 -0.0561 0.9796 0.0141
-5.000 -0.1703 0.03766 0.03558 -0.0708 0.9576 0.0134
-4.750 -0.1349 0.02944 0.02697 -0.0759 0.9354 0.0148
-4.500 -0.1033 0.03473 0.03238 -0.0749 0.9145 0.0194
-4.250 -0.0855 0.02818 0.02546 -0.0762 0.8883 0.0170
-4.000 -0.0616 0.02288 0.01971 -0.0761 0.8701 0.0176
-3.750 -0.0400 0.01616 0.01220 -0.0748 0.8556 0.0206
-3.500 -0.0138 0.01782 0.01402 -0.0750 0.8425 0.0217
-3.250 0.0126 0.01923 0.01551 -0.0750 0.8301 0.0253
-3.000 0.0364 0.01558 0.01137 -0.0740 0.8183 0.0246
-2.750 0.0615 0.01387 0.00933 -0.0732 0.8048 0.0256
-2.250 0.1121 0.01210 0.00713 -0.0723 0.7767 0.0306
-2.000 0.1382 0.01162 0.00657 -0.0720 0.7634 0.0321
-1.750 0.1644 0.01016 0.00478 -0.0712 0.7501 0.0302
-1.500 0.1907 0.00977 0.00431 -0.0708 0.7360 0.0316
-1.250 0.2170 0.00913 0.00353 -0.0703 0.7222 0.0319
-1.000 0.2434 0.00873 0.00305 -0.0700 0.7096 0.0329
-0.750 0.2699 0.00839 0.00264 -0.0696 0.6982 0.0335
-0.500 0.2962 0.00808 0.00226 -0.0692 0.6880 0.0336
-0.250 0.3227 0.00780 0.00194 -0.0688 0.6786 0.0336
0.000 0.3492 0.00757 0.00166 -0.0684 0.6701 0.0335
0.250 0.3757 0.00742 0.00147 -0.0681 0.6623 0.0342
0.500 0.4025 0.00726 0.00128 -0.0678 0.6558 0.0342
0.750 0.4293 0.00713 0.00112 -0.0675 0.6492 0.0344
1.000 0.4562 0.00704 0.00100 -0.0672 0.6430 0.0351
1.250 0.4832 0.00697 0.00092 -0.0669 0.6365 0.0370
1.500 0.5101 0.00696 0.00089 -0.0667 0.6306 0.0385
1.750 0.5370 0.00694 0.00084 -0.0664 0.6201 0.0412
2.000 0.5639 0.00694 0.00084 -0.0661 0.6091 0.0464
2.250 0.5891 0.00658 0.00095 -0.0657 0.5992 0.2678
2.500 0.6414 0.00508 0.00110 -0.0720 0.5803 1.0000
2.750 0.6671 0.00520 0.00114 -0.0714 0.5588 1.0000
3.000 0.6926 0.00533 0.00121 -0.0709 0.5326 1.0000
3.250 0.7172 0.00555 0.00128 -0.0702 0.4907 1.0000
3.500 0.7401 0.00597 0.00144 -0.0693 0.4298 1.0000
3.750 0.7626 0.00646 0.00167 -0.0684 0.3696 1.0000
4.000 0.7850 0.00698 0.00192 -0.0675 0.3066 1.0000
4.250 0.8023 0.00812 0.00240 -0.0659 0.1614 1.0000
4.500 0.8222 0.00899 0.00286 -0.0647 0.0753 1.0000
4.750 0.8462 0.00936 0.00313 -0.0640 0.0571 1.0000
5.000 0.8710 0.00961 0.00339 -0.0635 0.0493 1.0000
5.250 0.8952 0.00994 0.00369 -0.0628 0.0401 1.0000
5.500 0.9199 0.01021 0.00392 -0.0623 0.0323 1.0000
5.750 0.9433 0.01064 0.00430 -0.0615 0.0211 1.0000
6.000 0.9673 0.01100 0.00468 -0.0608 0.0177 1.0000
6.250 0.9896 0.01160 0.00531 -0.0598 0.0143 1.0000
6.500 1.0128 0.01204 0.00582 -0.0590 0.0131 1.0000
6.750 1.0362 0.01244 0.00626 -0.0582 0.0120 1.0000
7.000 1.0588 0.01293 0.00679 -0.0574 0.0110 1.0000
7.250 1.0801 0.01359 0.00750 -0.0563 0.0101 1.0000
7.500 1.0952 0.01503 0.00911 -0.0541 0.0092 1.0000
7.750 1.1157 0.01578 0.00996 -0.0530 0.0089 1.0000
8.000 1.1367 0.01645 0.01070 -0.0519 0.0086 1.0000
8.250 1.1574 0.01715 0.01148 -0.0508 0.0081 1.0000
8.500 1.1778 0.01788 0.01228 -0.0497 0.0075 1.0000
8.750 1.1985 0.01852 0.01298 -0.0487 0.0070 1.0000
9.000 1.2181 0.01929 0.01380 -0.0476 0.0067 1.0000
9.250 1.2356 0.02037 0.01500 -0.0462 0.0064 1.0000
9.500 1.2495 0.02214 0.01693 -0.0442 0.0062 1.0000
9.750 1.2592 0.02496 0.02002 -0.0419 0.0059 1.0000
10.000 1.2659 0.02830 0.02371 -0.0393 0.0057 1.0000
10.250 1.2796 0.02967 0.02527 -0.0375 0.0057 1.0000
10.500 1.2907 0.03128 0.02708 -0.0356 0.0055 1.0000
10.750 1.2987 0.03313 0.02913 -0.0333 0.0054 1.0000
11.000 1.3005 0.03548 0.03173 -0.0304 0.0053 1.0000
11.250 1.2919 0.03814 0.03463 -0.0262 0.0052 1.0000
11.500 1.2837 0.04061 0.03732 -0.0227 0.0050 1.0000
11.750 1.2664 0.04423 0.04120 -0.0195 0.0050 1.0000
12.000 1.2458 0.04855 0.04577 -0.0175 0.0049 1.0000
12.250 1.2267 0.05310 0.05053 -0.0169 0.0049 1.0000
12.500 1.1979 0.05959 0.05725 -0.0177 0.0049 1.0000
12.750 1.1737 0.06618 0.06403 -0.0201 0.0050 1.0000
13.000 1.1479 0.07385 0.07187 -0.0239 0.0050 1.0000
13.250 1.1257 0.08184 0.08000 -0.0287 0.0051 1.0000
13.500 1.0990 0.09231 0.09061 -0.0357 0.0052 1.0000
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Polar data table (+)
Polar graphs
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