GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 6K AIRFOIL (goe06k-il) Reynolds number: 100,000 Max Cl/Cd: 44.57 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe06k-il-100000-n5.txt Download as CSV file: xf-goe06k-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 6K 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4709 0.10411 0.09956 -0.0290 1.0000 0.0357
-7.750 -0.4817 0.10213 0.09766 -0.0277 1.0000 0.0358
-7.500 -0.4934 0.10004 0.09564 -0.0273 1.0000 0.0358
-7.250 -0.4992 0.09727 0.09291 -0.0280 1.0000 0.0359
-7.000 -0.5023 0.09419 0.08985 -0.0290 1.0000 0.0360
-6.750 -0.4883 0.08897 0.08461 -0.0342 0.9966 0.0362
-6.500 -0.4810 0.08462 0.08028 -0.0320 0.9948 0.0370
-6.250 -0.4676 0.08042 0.07604 -0.0344 0.9912 0.0380
-6.000 -0.4501 0.07592 0.07146 -0.0386 0.9876 0.0397
-5.750 -0.4322 0.07147 0.06690 -0.0430 0.9829 0.0420
-5.500 -0.3972 0.06729 0.06220 -0.0521 0.9774 0.0445
-5.250 -0.3870 0.06180 0.05674 -0.0526 0.9737 0.0454
-5.000 -0.3739 0.05807 0.05304 -0.0526 0.9708 0.0477
-4.750 -0.3496 0.05385 0.04860 -0.0552 0.9681 0.0489
-4.500 -0.3228 0.04770 0.04189 -0.0556 0.9634 0.0252
-4.250 -0.3029 0.04378 0.03774 -0.0561 0.9599 0.0235
-4.000 -0.2774 0.03999 0.03353 -0.0569 0.9572 0.0222
-3.750 -0.2523 0.03650 0.02958 -0.0569 0.9548 0.0211
-3.500 -0.2321 0.03358 0.02620 -0.0554 0.9508 0.0208
-3.250 -0.2071 0.03115 0.02326 -0.0547 0.9477 0.0222
-3.000 -0.1791 0.02883 0.02038 -0.0543 0.9453 0.0233
-2.750 -0.1496 0.02673 0.01774 -0.0541 0.9435 0.0236
-2.500 -0.1188 0.02498 0.01548 -0.0540 0.9421 0.0255
-2.250 -0.0962 0.02368 0.01401 -0.0530 0.9390 0.0289
-2.000 -0.0723 0.02266 0.01284 -0.0520 0.9355 0.0321
-1.750 -0.0459 0.02181 0.01186 -0.0517 0.9326 0.0390
-1.500 -0.0184 0.02109 0.01104 -0.0516 0.9301 0.0518
-1.250 0.0104 0.02043 0.01033 -0.0519 0.9282 0.0800
-1.000 0.0947 0.01754 0.01015 -0.0649 0.9344 1.0000
-0.750 0.1228 0.01769 0.00997 -0.0652 0.9313 1.0000
-0.500 0.1538 0.01785 0.00985 -0.0662 0.9288 1.0000
-0.250 0.1783 0.01801 0.00981 -0.0658 0.9246 1.0000
0.000 0.2011 0.01818 0.00982 -0.0651 0.9199 1.0000
0.250 0.2294 0.01836 0.00985 -0.0655 0.9168 1.0000
0.500 0.2609 0.01854 0.00991 -0.0666 0.9143 1.0000
0.750 0.2823 0.01875 0.01004 -0.0657 0.9093 1.0000
1.000 0.3060 0.01896 0.01019 -0.0652 0.9048 1.0000
1.250 0.3358 0.01914 0.01033 -0.0659 0.9015 1.0000
1.500 0.3681 0.01931 0.01049 -0.0672 0.8991 1.0000
1.750 0.3858 0.01954 0.01074 -0.0655 0.8920 1.0000
2.000 0.4179 0.01960 0.01083 -0.0665 0.8872 1.0000
2.250 0.4553 0.01960 0.01089 -0.0686 0.8840 1.0000
2.500 0.4725 0.01980 0.01116 -0.0666 0.8750 1.0000
2.750 0.5058 0.01985 0.01133 -0.0679 0.8713 1.0000
3.000 0.5268 0.02007 0.01165 -0.0668 0.8641 1.0000
3.250 0.5564 0.02015 0.01190 -0.0672 0.8588 1.0000
3.500 0.5935 0.02008 0.01204 -0.0690 0.8555 1.0000
3.750 0.6120 0.02022 0.01238 -0.0672 0.8449 1.0000
4.000 0.6455 0.01967 0.01210 -0.0675 0.8321 1.0000
4.250 0.6904 0.01801 0.01079 -0.0684 0.8093 1.0000
4.500 0.7220 0.01620 0.00919 -0.0659 0.7488 1.0000
4.750 0.7558 0.01911 0.00826 -0.0657 0.0727 1.0000
5.000 0.7690 0.02042 0.00939 -0.0628 0.0378 1.0000
5.250 0.7835 0.02148 0.01052 -0.0601 0.0286 1.0000
5.500 0.7963 0.02265 0.01186 -0.0571 0.0254 1.0000
5.750 0.8109 0.02380 0.01317 -0.0545 0.0221 1.0000
6.000 0.8286 0.02542 0.01488 -0.0526 0.0199 1.0000
6.250 0.8626 0.02850 0.01805 -0.0540 0.0180 1.0000
6.500 0.8942 0.03044 0.02036 -0.0542 0.0162 1.0000
6.750 0.9271 0.03338 0.02370 -0.0547 0.0156 1.0000
7.000 0.9526 0.03658 0.02738 -0.0536 0.0154 1.0000
7.250 0.9709 0.03988 0.03118 -0.0514 0.0155 1.0000
7.500 0.9832 0.04300 0.03478 -0.0484 0.0152 1.0000
7.750 0.9917 0.04593 0.03810 -0.0450 0.0148 1.0000
8.000 0.9971 0.04874 0.04126 -0.0415 0.0143 1.0000
8.250 1.0001 0.05148 0.04425 -0.0382 0.0138 1.0000
8.500 0.9972 0.05536 0.04861 -0.0332 0.0143 1.0000
8.750 0.9912 0.05916 0.05277 -0.0285 0.0148 1.0000
9.000 0.9825 0.06269 0.05658 -0.0239 0.0152 1.0000
9.250 0.9704 0.06580 0.05990 -0.0193 0.0156 1.0000
9.500 0.9549 0.06905 0.06334 -0.0148 0.0159 1.0000
9.750 0.9390 0.07236 0.06681 -0.0111 0.0161 1.0000
10.000 0.9237 0.07568 0.07027 -0.0084 0.0164 1.0000
10.250 0.9060 0.07950 0.07423 -0.0065 0.0166 1.0000
10.500 0.8881 0.08374 0.07858 -0.0057 0.0167 1.0000
10.750 0.8716 0.08828 0.08322 -0.0061 0.0169 1.0000
11.000 0.8551 0.09353 0.08855 -0.0077 0.0170 1.0000
11.250 0.8407 0.09944 0.09452 -0.0106 0.0171 1.0000
11.500 0.8292 0.10603 0.10114 -0.0144 0.0174 1.0000
11.750 0.8212 0.11190 0.10699 -0.0171 0.0179 1.0000
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Polar data table (+)
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