GOE 15 AIRFOIL (goe15-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 15 AIRFOIL (goe15-il) Reynolds number: 500,000 Max Cl/Cd: 94.27 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe15-il-500000-n5.txt Download as CSV file: xf-goe15-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 15 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.0260 0.09337 0.09042 -0.0908 0.8469 0.0197
-9.500 0.0332 0.09096 0.08785 -0.0918 0.8117 0.0210
-9.250 0.0382 0.08884 0.08558 -0.0921 0.7814 0.0210
-9.000 0.0431 0.08678 0.08340 -0.0923 0.7598 0.0211
-8.750 0.0483 0.08460 0.08115 -0.0927 0.7463 0.0211
-8.500 0.0557 0.08251 0.07899 -0.0927 0.7352 0.0213
-8.250 0.0633 0.08059 0.07704 -0.0928 0.7260 0.0214
-8.000 0.0712 0.07890 0.07531 -0.0929 0.7177 0.0219
-7.750 0.0785 0.07719 0.07359 -0.0930 0.7103 0.0227
-7.500 0.0822 0.07528 0.07166 -0.0931 0.7041 0.0239
-7.250 0.0840 0.07344 0.06983 -0.0931 0.6990 0.0240
-7.000 0.0909 0.07132 0.06769 -0.0941 0.6935 0.0241
-6.750 0.0996 0.06906 0.06541 -0.0957 0.6878 0.0241
-6.500 0.1104 0.06672 0.06303 -0.0975 0.6828 0.0242
-6.250 0.1232 0.06435 0.06064 -0.0994 0.6767 0.0242
-6.000 0.1354 0.06230 0.05857 -0.0992 0.6708 0.0244
-5.750 0.1500 0.06058 0.05683 -0.0999 0.6651 0.0250
-5.500 0.1662 0.05867 0.05491 -0.1011 0.6589 0.0257
-5.250 0.1837 0.05656 0.05274 -0.1027 0.6525 0.0269
-5.000 0.2037 0.05418 0.05030 -0.1050 0.6465 0.0272
-4.750 0.2246 0.05187 0.04793 -0.1070 0.6389 0.0273
-4.500 0.2456 0.04966 0.04563 -0.1087 0.6309 0.0273
-4.000 0.2839 0.04552 0.04137 -0.1101 0.6096 0.0277
-3.750 0.3040 0.04387 0.03963 -0.1107 0.5958 0.0281
-3.500 0.3253 0.04223 0.03788 -0.1113 0.5802 0.0286
-3.250 0.3475 0.04061 0.03613 -0.1118 0.5622 0.0294
-3.000 0.3726 0.03888 0.03422 -0.1127 0.5418 0.0305
-2.750 0.3975 0.03720 0.03233 -0.1132 0.5202 0.0306
-2.500 0.4223 0.03562 0.03053 -0.1135 0.4994 0.0307
-2.250 0.4472 0.03404 0.02874 -0.1137 0.4818 0.0308
-2.000 0.4690 0.03246 0.02703 -0.1135 0.4685 0.0308
-1.750 0.4879 0.03117 0.02568 -0.1130 0.4582 0.0311
-1.500 0.5106 0.03004 0.02444 -0.1128 0.4497 0.0315
-1.250 0.5344 0.02893 0.02322 -0.1126 0.4427 0.0319
-1.000 0.5590 0.02784 0.02202 -0.1124 0.4363 0.0328
-0.500 0.6128 0.02556 0.01940 -0.1115 0.4252 0.0342
-0.250 0.6378 0.02438 0.01810 -0.1110 0.4208 0.0342
0.000 0.6595 0.02337 0.01705 -0.1106 0.4165 0.0333
0.250 0.6843 0.02229 0.01582 -0.1100 0.4126 0.0325
0.500 0.7091 0.02136 0.01475 -0.1093 0.4087 0.0325
0.750 0.7348 0.02047 0.01375 -0.1087 0.4055 0.0328
1.000 0.7603 0.01965 0.01281 -0.1080 0.4018 0.0330
1.250 0.7875 0.01846 0.01136 -0.1068 0.3986 0.0343
1.500 0.8114 0.01796 0.01080 -0.1062 0.3954 0.0346
1.750 0.8354 0.01758 0.01034 -0.1056 0.3922 0.0349
2.000 0.8603 0.01714 0.00984 -0.1050 0.3894 0.0354
2.250 0.8856 0.01666 0.00929 -0.1043 0.3865 0.0359
2.500 0.9108 0.01620 0.00874 -0.1036 0.3833 0.0366
2.750 0.9366 0.01537 0.00769 -0.1025 0.3805 0.0382
3.000 0.9605 0.01518 0.00745 -0.1018 0.3772 0.0386
3.250 0.9841 0.01504 0.00727 -0.1011 0.3731 0.0390
3.500 1.0092 0.01479 0.00700 -0.1005 0.3691 0.0396
3.750 1.0337 0.01456 0.00672 -0.0998 0.3652 0.0406
4.000 1.0581 0.01416 0.00621 -0.0988 0.3618 0.0422
4.250 1.0813 0.01400 0.00600 -0.0980 0.3581 0.0428
4.500 1.1049 0.01396 0.00596 -0.0972 0.3541 0.0433
4.750 1.1287 0.01387 0.00590 -0.0965 0.3500 0.0441
5.000 1.1518 0.01383 0.00585 -0.0956 0.3460 0.0453
5.250 1.1741 0.01380 0.00578 -0.0945 0.3426 0.0467
5.500 1.1955 0.01380 0.00575 -0.0933 0.3394 0.0474
5.750 1.2183 0.01378 0.00578 -0.0924 0.3367 0.0481
6.000 1.2407 0.01381 0.00586 -0.0915 0.3334 0.0489
6.250 1.2624 0.01388 0.00595 -0.0904 0.3298 0.0502
6.500 1.2829 0.01399 0.00606 -0.0891 0.3260 0.0518
6.750 1.3017 0.01411 0.00618 -0.0875 0.3223 0.0525
7.000 1.3221 0.01416 0.00627 -0.0861 0.3184 0.0533
7.250 1.3414 0.01427 0.00642 -0.0846 0.3137 0.0544
7.500 1.3597 0.01445 0.00661 -0.0830 0.3093 0.0555
7.750 1.3781 0.01465 0.00684 -0.0814 0.3053 0.0580
8.000 1.3980 0.01483 0.00706 -0.0801 0.3009 0.0592
8.250 1.4161 0.01504 0.00729 -0.0785 0.2958 0.0607
8.500 1.4326 0.01534 0.00758 -0.0766 0.2908 0.0627
8.750 1.4515 0.01557 0.00786 -0.0753 0.2860 0.0653
9.000 1.4681 0.01588 0.00818 -0.0735 0.2790 0.0695
9.250 1.4829 0.01627 0.00855 -0.0716 0.2698 0.0736
9.500 1.4954 0.01676 0.00902 -0.0693 0.2587 0.0857
10.000 1.5603 0.01716 0.01049 -0.0740 0.2312 1.0000
10.250 1.5724 0.01780 0.01110 -0.0720 0.2204 1.0000
10.500 1.5829 0.01856 0.01183 -0.0698 0.2097 1.0000
10.750 1.5921 0.01943 0.01266 -0.0676 0.1992 1.0000
11.000 1.6005 0.02039 0.01357 -0.0655 0.1877 1.0000
11.250 1.6090 0.02138 0.01454 -0.0635 0.1782 1.0000
11.750 1.6260 0.02350 0.01666 -0.0598 0.1639 1.0000
12.000 1.6321 0.02479 0.01794 -0.0580 0.1567 1.0000
12.250 1.6407 0.02596 0.01914 -0.0565 0.1504 1.0000
12.500 1.6463 0.02741 0.02059 -0.0549 0.1434 1.0000
12.750 1.6532 0.02881 0.02203 -0.0535 0.1380 1.0000
13.000 1.6584 0.03042 0.02365 -0.0522 0.1306 1.0000
13.250 1.6607 0.03232 0.02556 -0.0509 0.1219 1.0000
13.500 1.6598 0.03458 0.02781 -0.0495 0.1118 1.0000
13.750 1.6517 0.03758 0.03075 -0.0481 0.0962 1.0000
14.000 1.6403 0.04102 0.03415 -0.0467 0.0825 1.0000
14.250 1.6236 0.04517 0.03825 -0.0455 0.0685 1.0000
14.500 1.6102 0.04917 0.04226 -0.0448 0.0581 1.0000
14.750 1.5887 0.05431 0.04738 -0.0442 0.0444 1.0000
15.000 1.5646 0.06004 0.05311 -0.0441 0.0299 1.0000
15.250 1.5442 0.06562 0.05874 -0.0444 0.0209 1.0000
15.500 1.5305 0.07050 0.06369 -0.0448 0.0179 1.0000
15.750 1.5217 0.07483 0.06812 -0.0452 0.0167 1.0000
16.000 1.5129 0.07923 0.07261 -0.0458 0.0158 1.0000
16.500 1.4976 0.08779 0.08138 -0.0471 0.0145 1.0000
16.750 1.4914 0.09192 0.08560 -0.0479 0.0141 1.0000
17.000 1.4847 0.09615 0.08994 -0.0487 0.0137 1.0000
17.250 1.4768 0.10060 0.09448 -0.0496 0.0133 1.0000
17.500 1.4698 0.10495 0.09893 -0.0507 0.0130 1.0000
17.750 1.4622 0.10947 0.10354 -0.0518 0.0126 1.0000
18.000 1.4534 0.11425 0.10842 -0.0532 0.0122 1.0000
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Polar data table (+)
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