GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 655 AIRFOIL (goe655-il) Reynolds number: 100,000 Max Cl/Cd: 45.64 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe655-il-100000.txt Download as CSV file: xf-goe655-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 655 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3152 0.10081 0.09630 -0.0325 1.0000 0.1449
-8.500 -0.3682 0.10118 0.09689 -0.0316 1.0000 0.1462
-8.250 -0.4118 0.10111 0.09699 -0.0288 1.0000 0.1465
-8.000 -0.3343 0.09478 0.09052 -0.0252 1.0000 0.1528
-7.750 -0.3494 0.09374 0.08959 -0.0223 1.0000 0.1560
-7.500 -0.3774 0.09312 0.08908 -0.0193 1.0000 0.1585
-7.250 -0.4166 0.09286 0.08897 -0.0160 1.0000 0.1600
-7.000 -0.4288 0.08820 0.08434 -0.0231 0.9941 0.1641
-6.750 -0.3930 0.08565 0.08177 -0.0216 0.9896 0.1699
-6.500 -0.3835 0.07917 0.07524 -0.0346 0.9765 0.1807
-6.250 -0.3502 0.07621 0.07226 -0.0359 0.9709 0.1865
-6.000 -0.3676 0.05122 0.04608 -0.0623 0.9552 0.1190
-5.750 -0.3571 0.04244 0.03605 -0.0644 0.9443 0.1020
-5.500 -0.3243 0.03868 0.03192 -0.0669 0.9380 0.1006
-5.250 -0.2974 0.03584 0.02864 -0.0676 0.9284 0.1002
-5.000 -0.2616 0.03367 0.02585 -0.0694 0.9209 0.1021
-4.750 -0.2266 0.03141 0.02320 -0.0709 0.9113 0.1035
-4.500 -0.1889 0.02955 0.02119 -0.0726 0.9018 0.1058
-4.250 -0.1426 0.02807 0.01957 -0.0754 0.8935 0.1110
-4.000 -0.1083 0.02696 0.01817 -0.0761 0.8828 0.1156
-3.750 -0.0604 0.02532 0.01657 -0.0792 0.8770 0.1220
-3.500 -0.0276 0.02454 0.01566 -0.0795 0.8667 0.1308
-3.250 0.0196 0.02323 0.01445 -0.0824 0.8610 0.1459
-3.000 0.0512 0.02226 0.01368 -0.0826 0.8511 0.1663
-2.750 0.0908 0.02090 0.01271 -0.0841 0.8442 0.2304
-2.500 0.1163 0.02011 0.01237 -0.0832 0.8329 0.3315
-2.250 0.1572 0.01929 0.01178 -0.0847 0.8263 0.4105
-2.000 0.1826 0.01888 0.01151 -0.0836 0.8135 0.4661
-1.750 0.2131 0.01826 0.01111 -0.0831 0.8028 0.5297
-1.500 0.2480 0.01738 0.01060 -0.0831 0.7937 0.6252
-1.250 0.2743 0.01671 0.01047 -0.0811 0.7807 0.7596
-1.000 0.3932 0.01595 0.00978 -0.0960 0.7689 0.9625
-0.750 0.4663 0.01561 0.00907 -0.1045 0.7527 1.0000
-0.500 0.4871 0.01556 0.00878 -0.1031 0.7361 1.0000
-0.250 0.5089 0.01558 0.00858 -0.1017 0.7192 1.0000
0.000 0.5310 0.01566 0.00844 -0.1003 0.7021 1.0000
0.250 0.5529 0.01577 0.00835 -0.0988 0.6846 1.0000
0.500 0.5748 0.01591 0.00830 -0.0974 0.6670 1.0000
0.750 0.5966 0.01607 0.00826 -0.0959 0.6495 1.0000
1.000 0.6186 0.01624 0.00825 -0.0945 0.6325 1.0000
1.250 0.6407 0.01644 0.00828 -0.0932 0.6163 1.0000
1.500 0.6632 0.01668 0.00835 -0.0919 0.6012 1.0000
1.750 0.6865 0.01694 0.00844 -0.0908 0.5876 1.0000
2.000 0.7118 0.01720 0.00850 -0.0901 0.5755 1.0000
2.250 0.7328 0.01754 0.00876 -0.0887 0.5623 1.0000
2.500 0.7549 0.01791 0.00903 -0.0876 0.5507 1.0000
2.750 0.7801 0.01824 0.00920 -0.0869 0.5407 1.0000
3.000 0.8022 0.01862 0.00951 -0.0858 0.5300 1.0000
3.250 0.8249 0.01902 0.00984 -0.0848 0.5203 1.0000
3.500 0.8504 0.01934 0.01001 -0.0842 0.5109 1.0000
3.750 0.8705 0.01975 0.01042 -0.0828 0.5006 1.0000
4.000 0.8969 0.02010 0.01060 -0.0824 0.4922 1.0000
4.250 0.9166 0.02052 0.01106 -0.0809 0.4827 1.0000
4.500 0.9424 0.02090 0.01133 -0.0805 0.4750 1.0000
4.750 0.9625 0.02136 0.01184 -0.0791 0.4665 1.0000
5.000 0.9906 0.02177 0.01209 -0.0791 0.4600 1.0000
5.250 1.0082 0.02229 0.01275 -0.0774 0.4518 1.0000
5.500 1.0351 0.02268 0.01302 -0.0772 0.4450 1.0000
5.750 1.0540 0.02326 0.01370 -0.0757 0.4376 1.0000
6.000 1.0779 0.02370 0.01413 -0.0751 0.4306 1.0000
6.250 1.1002 0.02426 0.01470 -0.0742 0.4237 1.0000
6.500 1.1208 0.02474 0.01523 -0.0730 0.4158 1.0000
6.750 1.1452 0.02524 0.01569 -0.0724 0.4085 1.0000
7.000 1.1634 0.02575 0.01629 -0.0709 0.4000 1.0000
7.250 1.1879 0.02624 0.01672 -0.0703 0.3923 1.0000
7.500 1.2052 0.02679 0.01738 -0.0687 0.3834 1.0000
7.750 1.2283 0.02736 0.01792 -0.0679 0.3754 1.0000
8.000 1.2461 0.02793 0.01856 -0.0664 0.3663 1.0000
8.250 1.2657 0.02862 0.01928 -0.0651 0.3576 1.0000
8.500 1.2871 0.02914 0.01979 -0.0641 0.3484 1.0000
8.750 1.3009 0.02998 0.02075 -0.0621 0.3391 1.0000
9.000 1.3279 0.03047 0.02111 -0.0620 0.3307 1.0000
9.250 1.3354 0.03150 0.02236 -0.0591 0.3219 1.0000
9.500 1.3629 0.03209 0.02284 -0.0591 0.3147 1.0000
9.750 1.3695 0.03332 0.02431 -0.0562 0.3075 1.0000
10.000 1.3880 0.03414 0.02518 -0.0551 0.3011 1.0000
10.250 1.4107 0.03513 0.02617 -0.0546 0.2957 1.0000
10.500 1.4122 0.03648 0.02779 -0.0512 0.2899 1.0000
10.750 1.4320 0.03726 0.02860 -0.0502 0.2849 1.0000
11.000 1.4549 0.03828 0.02964 -0.0499 0.2804 1.0000
11.250 1.4482 0.04006 0.03174 -0.0457 0.2764 1.0000
11.500 1.4529 0.04152 0.03337 -0.0430 0.2724 1.0000
11.750 1.4769 0.04223 0.03409 -0.0428 0.2685 1.0000
12.000 1.4875 0.04347 0.03542 -0.0409 0.2646 1.0000
12.250 1.4630 0.04579 0.03803 -0.0350 0.2618 1.0000
12.500 1.4505 0.04769 0.04011 -0.0309 0.2581 1.0000
12.750 1.5105 0.04566 0.03783 -0.0338 0.2504 1.0000
13.000 1.4777 0.04867 0.04116 -0.0281 0.2483 1.0000
13.250 1.4406 0.05273 0.04550 -0.0235 0.2467 1.0000
13.500 1.3528 0.06252 0.05564 -0.0196 0.2480 1.0000
13.750 1.4990 0.05147 0.04416 -0.0229 0.2353 1.0000
14.000 1.4510 0.05680 0.04981 -0.0191 0.2343 1.0000
14.250 1.3690 0.06722 0.06056 -0.0173 0.2354 1.0000
14.750 1.4743 0.06007 0.05329 -0.0161 0.2214 1.0000
15.000 1.4027 0.06991 0.06342 -0.0155 0.2219 1.0000
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Polar data table (+)
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