GOE 515 AIRFOIL (goe515-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 515 AIRFOIL (goe515-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.11 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe515-il-1000000-n5.txt Download as CSV file: xf-goe515-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 515 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.7789 0.08150 0.07939 -0.0398 1.0000 0.0061
-13.250 -0.8401 0.06824 0.06604 -0.0491 1.0000 0.0057
-13.000 -1.0490 0.03032 0.02731 -0.0693 1.0000 0.0049
-12.750 -1.0443 0.02787 0.02466 -0.0677 1.0000 0.0050
-12.500 -1.0355 0.02610 0.02273 -0.0660 1.0000 0.0051
-12.250 -1.0256 0.02456 0.02104 -0.0640 1.0000 0.0051
-12.000 -1.0104 0.02321 0.01953 -0.0629 0.9996 0.0053
-11.750 -0.9865 0.02147 0.01760 -0.0638 0.9975 0.0055
-11.500 -0.9612 0.02002 0.01600 -0.0646 0.9951 0.0058
-11.250 -0.9361 0.01892 0.01477 -0.0650 0.9926 0.0061
-11.000 -0.9100 0.01797 0.01370 -0.0654 0.9900 0.0063
-10.750 -0.8825 0.01711 0.01272 -0.0661 0.9877 0.0067
-10.500 -0.8536 0.01634 0.01183 -0.0669 0.9859 0.0070
-10.250 -0.8260 0.01567 0.01106 -0.0672 0.9832 0.0073
-10.000 -0.7988 0.01496 0.01024 -0.0676 0.9799 0.0078
-9.750 -0.7697 0.01422 0.00942 -0.0683 0.9774 0.0086
-9.500 -0.7392 0.01360 0.00872 -0.0693 0.9752 0.0094
-9.250 -0.7111 0.01310 0.00815 -0.0696 0.9710 0.0101
-9.000 -0.6816 0.01256 0.00753 -0.0702 0.9665 0.0114
-8.500 -0.6224 0.01165 0.00653 -0.0713 0.9546 0.0147
-8.000 -0.5658 0.01100 0.00583 -0.0717 0.9404 0.0194
-7.750 -0.5379 0.01072 0.00550 -0.0718 0.9332 0.0206
-7.500 -0.5117 0.01043 0.00518 -0.0715 0.9243 0.0225
-7.250 -0.4850 0.01020 0.00489 -0.0712 0.9159 0.0240
-7.000 -0.4586 0.01000 0.00462 -0.0709 0.9066 0.0254
-6.750 -0.4321 0.00982 0.00439 -0.0706 0.8976 0.0264
-6.500 -0.4055 0.00967 0.00417 -0.0702 0.8888 0.0270
-6.250 -0.3792 0.00949 0.00392 -0.0699 0.8798 0.0277
-6.000 -0.3534 0.00921 0.00356 -0.0694 0.8717 0.0295
-5.750 -0.3273 0.00898 0.00330 -0.0690 0.8635 0.0314
-5.500 -0.3010 0.00880 0.00308 -0.0686 0.8560 0.0329
-5.250 -0.2745 0.00864 0.00286 -0.0683 0.8487 0.0339
-5.000 -0.2479 0.00848 0.00264 -0.0679 0.8423 0.0347
-4.750 -0.2212 0.00834 0.00245 -0.0676 0.8355 0.0354
-4.500 -0.1945 0.00821 0.00227 -0.0673 0.8294 0.0362
-4.250 -0.1678 0.00804 0.00208 -0.0669 0.8232 0.0394
-3.750 -0.1145 0.00773 0.00176 -0.0663 0.8117 0.0503
-3.500 -0.0880 0.00757 0.00164 -0.0660 0.8056 0.0621
-3.250 -0.0612 0.00746 0.00154 -0.0657 0.8002 0.0726
-3.000 -0.0342 0.00737 0.00147 -0.0654 0.7929 0.0809
-2.750 -0.0075 0.00732 0.00139 -0.0650 0.7821 0.0856
-2.500 0.0188 0.00727 0.00131 -0.0646 0.7679 0.0901
-2.250 0.0453 0.00724 0.00123 -0.0642 0.7541 0.0934
-2.000 0.0721 0.00722 0.00116 -0.0639 0.7434 0.0956
-1.750 0.0993 0.00717 0.00110 -0.0636 0.7349 0.0986
-1.500 0.1261 0.00712 0.00104 -0.0633 0.7255 0.1031
-1.250 0.1530 0.00708 0.00098 -0.0630 0.7156 0.1066
-1.000 0.1800 0.00706 0.00094 -0.0627 0.7054 0.1096
-0.750 0.2068 0.00705 0.00090 -0.0624 0.6939 0.1114
-0.500 0.2333 0.00702 0.00086 -0.0620 0.6823 0.1183
-0.250 0.2600 0.00700 0.00084 -0.0617 0.6709 0.1247
0.000 0.2862 0.00701 0.00083 -0.0613 0.6561 0.1325
0.250 0.3117 0.00703 0.00082 -0.0607 0.6337 0.1460
0.500 0.3373 0.00702 0.00084 -0.0602 0.6152 0.1725
0.750 0.3632 0.00702 0.00086 -0.0598 0.5993 0.1989
1.000 0.3889 0.00704 0.00089 -0.0593 0.5810 0.2212
1.250 0.4146 0.00707 0.00093 -0.0588 0.5606 0.2458
1.500 0.4398 0.00711 0.00097 -0.0582 0.5376 0.2750
1.750 0.4642 0.00716 0.00104 -0.0576 0.5074 0.3167
2.250 0.5082 0.00696 0.00123 -0.0554 0.4443 0.5492
2.500 0.5604 0.00626 0.00152 -0.0611 0.4031 0.9667
2.750 0.5954 0.00655 0.00168 -0.0627 0.3718 0.9842
3.000 0.6318 0.00685 0.00183 -0.0647 0.3385 0.9910
3.250 0.6664 0.00713 0.00198 -0.0664 0.3075 0.9955
3.500 0.7019 0.00738 0.00211 -0.0682 0.2809 0.9984
3.750 0.7330 0.00774 0.00228 -0.0692 0.2376 1.0000
4.000 0.7515 0.00828 0.00254 -0.0675 0.1764 1.0000
4.250 0.7724 0.00864 0.00277 -0.0661 0.1477 1.0000
4.500 0.7945 0.00891 0.00297 -0.0650 0.1310 1.0000
4.750 0.8170 0.00915 0.00316 -0.0639 0.1187 1.0000
5.000 0.8394 0.00940 0.00335 -0.0628 0.1063 1.0000
5.250 0.8618 0.00965 0.00355 -0.0617 0.0947 1.0000
5.500 0.8824 0.01003 0.00381 -0.0604 0.0704 1.0000
5.750 0.9037 0.01037 0.00407 -0.0591 0.0555 1.0000
6.000 0.9253 0.01068 0.00434 -0.0579 0.0461 1.0000
6.250 0.9468 0.01100 0.00462 -0.0567 0.0382 1.0000
6.500 0.9681 0.01133 0.00491 -0.0555 0.0306 1.0000
6.750 0.9887 0.01171 0.00525 -0.0541 0.0216 1.0000
7.000 1.0096 0.01208 0.00558 -0.0528 0.0167 1.0000
7.250 1.0308 0.01241 0.00592 -0.0516 0.0137 1.0000
7.500 1.0520 0.01276 0.00627 -0.0504 0.0122 1.0000
7.750 1.0724 0.01315 0.00667 -0.0490 0.0106 1.0000
8.000 1.0933 0.01350 0.00706 -0.0478 0.0098 1.0000
8.250 1.1141 0.01385 0.00744 -0.0465 0.0093 1.0000
8.500 1.1344 0.01422 0.00785 -0.0452 0.0087 1.0000
8.750 1.1540 0.01465 0.00829 -0.0438 0.0080 1.0000
9.000 1.1724 0.01516 0.00884 -0.0422 0.0073 1.0000
9.250 1.1918 0.01558 0.00928 -0.0407 0.0070 1.0000
9.500 1.2109 0.01599 0.00974 -0.0393 0.0067 1.0000
9.750 1.2291 0.01647 0.01028 -0.0377 0.0063 1.0000
10.000 1.2471 0.01693 0.01078 -0.0361 0.0060 1.0000
10.250 1.2641 0.01745 0.01134 -0.0344 0.0058 1.0000
10.500 1.2801 0.01798 0.01191 -0.0325 0.0056 1.0000
10.750 1.2930 0.01857 0.01255 -0.0301 0.0053 1.0000
11.000 1.3034 0.01929 0.01334 -0.0273 0.0050 1.0000
11.250 1.3146 0.02000 0.01411 -0.0247 0.0049 1.0000
11.500 1.3284 0.02056 0.01473 -0.0227 0.0048 1.0000
11.750 1.3403 0.02128 0.01554 -0.0205 0.0047 1.0000
12.000 1.3535 0.02193 0.01624 -0.0186 0.0046 1.0000
12.250 1.3623 0.02291 0.01731 -0.0162 0.0045 1.0000
12.500 1.3746 0.02366 0.01813 -0.0144 0.0043 1.0000
12.750 1.3837 0.02466 0.01921 -0.0124 0.0042 1.0000
13.000 1.3951 0.02552 0.02013 -0.0107 0.0040 1.0000
13.250 1.4036 0.02663 0.02132 -0.0089 0.0040 1.0000
13.500 1.4143 0.02761 0.02235 -0.0074 0.0038 1.0000
13.750 1.4203 0.02899 0.02382 -0.0057 0.0037 1.0000
14.000 1.4259 0.03047 0.02540 -0.0041 0.0036 1.0000
14.250 1.4291 0.03222 0.02724 -0.0026 0.0035 1.0000
14.500 1.4309 0.03416 0.02929 -0.0013 0.0035 1.0000
14.750 1.4297 0.03649 0.03173 -0.0001 0.0034 1.0000
15.000 1.4271 0.03907 0.03444 0.0009 0.0033 1.0000
15.250 1.4312 0.04108 0.03654 0.0014 0.0033 1.0000
15.500 1.4272 0.04404 0.03962 0.0018 0.0033 1.0000
15.750 1.4199 0.04757 0.04330 0.0019 0.0033 1.0000
16.000 1.4200 0.05037 0.04620 0.0017 0.0032 1.0000
16.250 1.4152 0.05393 0.04989 0.0011 0.0032 1.0000
16.500 1.4051 0.05841 0.05450 0.0000 0.0032 1.0000
16.750 1.3940 0.06329 0.05952 -0.0015 0.0032 1.0000
17.000 1.3837 0.06829 0.06465 -0.0034 0.0031 1.0000
17.250 1.3658 0.07481 0.07132 -0.0062 0.0032 1.0000
17.500 1.3502 0.08119 0.07784 -0.0090 0.0031 1.0000
17.750 1.3311 0.08838 0.08517 -0.0124 0.0031 1.0000
18.000 1.3096 0.09624 0.09317 -0.0161 0.0031 1.0000
18.250 1.2796 0.10587 0.10295 -0.0209 0.0032 1.0000
18.500 1.2550 0.11480 0.11202 -0.0253 0.0031 1.0000
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