GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 585 AIRFOIL (goe585-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.25 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe585-il-1000000.txt Download as CSV file: xf-goe585-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 585 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3536 0.13976 0.13808 -0.0172 1.0000 0.0126
-13.250 -0.3490 0.13725 0.13557 -0.0179 1.0000 0.0128
-13.000 -0.4726 0.14273 0.14093 -0.0087 1.0000 0.0123
-12.750 -0.4662 0.13983 0.13803 -0.0095 1.0000 0.0124
-12.500 -0.4583 0.13761 0.13582 -0.0101 1.0000 0.0128
-12.250 -0.4525 0.13461 0.13282 -0.0111 1.0000 0.0130
-12.000 -0.4474 0.13133 0.12955 -0.0121 1.0000 0.0133
-9.500 -0.7288 0.02609 0.02334 -0.0599 0.9983 0.0149
-9.250 -0.7011 0.02388 0.02084 -0.0618 0.9965 0.0153
-9.000 -0.6758 0.02074 0.01730 -0.0637 0.9946 0.0161
-8.750 -0.6434 0.02087 0.01747 -0.0648 0.9934 0.0164
-8.500 -0.6125 0.02076 0.01735 -0.0656 0.9914 0.0168
-8.250 -0.5807 0.02074 0.01733 -0.0665 0.9896 0.0174
-8.000 -0.5498 0.02003 0.01651 -0.0676 0.9877 0.0181
-7.750 -0.5186 0.01914 0.01543 -0.0688 0.9861 0.0189
-7.500 -0.4852 0.01886 0.01503 -0.0701 0.9849 0.0194
-7.250 -0.4571 0.01625 0.01211 -0.0715 0.9836 0.0204
-7.000 -0.4303 0.01589 0.01173 -0.0714 0.9797 0.0210
-6.750 -0.3991 0.01569 0.01151 -0.0722 0.9772 0.0217
-6.500 -0.3670 0.01526 0.01103 -0.0733 0.9753 0.0226
-6.250 -0.3344 0.01461 0.01025 -0.0744 0.9737 0.0234
-6.000 -0.3008 0.01412 0.00966 -0.0756 0.9725 0.0241
-5.750 -0.2659 0.01397 0.00943 -0.0770 0.9714 0.0245
-5.500 -0.2423 0.01193 0.00719 -0.0766 0.9662 0.0259
-5.250 -0.2115 0.01143 0.00666 -0.0773 0.9626 0.0268
-5.000 -0.1793 0.01092 0.00609 -0.0782 0.9595 0.0274
-4.750 -0.1481 0.01044 0.00557 -0.0788 0.9537 0.0282
-4.500 -0.1169 0.01002 0.00510 -0.0793 0.9453 0.0291
-4.250 -0.0876 0.00960 0.00460 -0.0794 0.9353 0.0297
-4.000 -0.0579 0.00921 0.00415 -0.0796 0.9262 0.0302
-3.750 -0.0300 0.00892 0.00379 -0.0794 0.9154 0.0307
-3.500 -0.0030 0.00870 0.00351 -0.0790 0.9042 0.0310
-3.250 0.0222 0.00811 0.00282 -0.0783 0.8923 0.0322
-3.000 0.0481 0.00780 0.00243 -0.0777 0.8797 0.0332
-2.750 0.0743 0.00758 0.00216 -0.0771 0.8672 0.0340
-2.500 0.1004 0.00741 0.00193 -0.0765 0.8536 0.0348
-2.250 0.1265 0.00728 0.00173 -0.0759 0.8387 0.0358
-2.000 0.1525 0.00716 0.00155 -0.0753 0.8214 0.0370
-1.750 0.1784 0.00708 0.00140 -0.0746 0.8016 0.0382
-1.500 0.2041 0.00704 0.00126 -0.0739 0.7805 0.0397
-1.250 0.2295 0.00697 0.00112 -0.0732 0.7594 0.0448
-1.000 0.2547 0.00685 0.00104 -0.0724 0.7400 0.0720
-0.750 0.2800 0.00676 0.00101 -0.0718 0.7219 0.1102
-0.500 0.3057 0.00672 0.00098 -0.0712 0.7051 0.1376
-0.250 0.3316 0.00666 0.00096 -0.0706 0.6896 0.1663
0.000 0.3564 0.00649 0.00097 -0.0700 0.6731 0.2463
0.250 0.3815 0.00637 0.00099 -0.0694 0.6547 0.3213
0.500 0.4061 0.00619 0.00101 -0.0687 0.6356 0.4138
0.750 0.4203 0.00525 0.00107 -0.0660 0.6164 0.7740
1.000 0.4779 0.00508 0.00121 -0.0722 0.5817 0.9791
1.250 0.5203 0.00536 0.00127 -0.0754 0.5318 0.9944
1.500 0.5609 0.00574 0.00133 -0.0783 0.4655 1.0000
1.750 0.5826 0.00600 0.00141 -0.0770 0.4275 1.0000
2.000 0.6052 0.00622 0.00150 -0.0758 0.4001 1.0000
2.250 0.6285 0.00641 0.00158 -0.0748 0.3781 1.0000
2.500 0.6519 0.00659 0.00167 -0.0738 0.3595 1.0000
2.750 0.6755 0.00676 0.00176 -0.0728 0.3431 1.0000
3.250 0.7232 0.00710 0.00196 -0.0710 0.3140 1.0000
3.500 0.7474 0.00725 0.00207 -0.0702 0.3022 1.0000
3.750 0.7716 0.00740 0.00218 -0.0693 0.2911 1.0000
4.000 0.7957 0.00758 0.00230 -0.0685 0.2790 1.0000
4.250 0.8196 0.00777 0.00244 -0.0676 0.2653 1.0000
4.750 0.8677 0.00814 0.00271 -0.0660 0.2417 1.0000
5.000 0.8918 0.00832 0.00286 -0.0652 0.2305 1.0000
5.250 0.9158 0.00852 0.00302 -0.0643 0.2208 1.0000
5.500 0.9398 0.00872 0.00319 -0.0635 0.2113 1.0000
5.750 0.9640 0.00891 0.00335 -0.0628 0.2016 1.0000
6.000 0.9879 0.00914 0.00354 -0.0620 0.1910 1.0000
6.250 1.0116 0.00937 0.00374 -0.0612 0.1812 1.0000
6.500 1.0359 0.00957 0.00393 -0.0604 0.1725 1.0000
6.750 1.0596 0.00982 0.00415 -0.0597 0.1618 1.0000
7.000 1.0830 0.01010 0.00438 -0.0588 0.1500 1.0000
7.250 1.1060 0.01040 0.00464 -0.0580 0.1359 1.0000
7.500 1.1279 0.01082 0.00495 -0.0569 0.1148 1.0000
7.750 1.1472 0.01147 0.00540 -0.0555 0.0840 1.0000
8.000 1.1668 0.01209 0.00591 -0.0542 0.0639 1.0000
8.250 1.1879 0.01259 0.00634 -0.0530 0.0523 1.0000
8.500 1.2089 0.01308 0.00679 -0.0519 0.0420 1.0000
8.750 1.2283 0.01372 0.00733 -0.0505 0.0282 1.0000
9.000 1.2477 0.01434 0.00792 -0.0492 0.0205 1.0000
9.250 1.2678 0.01489 0.00847 -0.0479 0.0178 1.0000
9.500 1.2876 0.01545 0.00906 -0.0466 0.0159 1.0000
9.750 1.3079 0.01593 0.00959 -0.0453 0.0149 1.0000
10.000 1.3268 0.01650 0.01020 -0.0440 0.0139 1.0000
10.250 1.3434 0.01725 0.01101 -0.0422 0.0129 1.0000
10.500 1.3601 0.01793 0.01178 -0.0404 0.0123 1.0000
10.750 1.3779 0.01848 0.01239 -0.0389 0.0118 1.0000
11.000 1.3940 0.01911 0.01308 -0.0371 0.0113 1.0000
11.250 1.4089 0.01974 0.01377 -0.0352 0.0109 1.0000
11.500 1.4202 0.02043 0.01453 -0.0326 0.0105 1.0000
11.750 1.4285 0.02126 0.01542 -0.0296 0.0100 1.0000
12.000 1.4281 0.02258 0.01685 -0.0256 0.0096 1.0000
12.250 1.4341 0.02359 0.01796 -0.0227 0.0094 1.0000
12.500 1.4441 0.02441 0.01885 -0.0205 0.0092 1.0000
12.750 1.4524 0.02535 0.01987 -0.0183 0.0090 1.0000
13.000 1.4573 0.02656 0.02117 -0.0158 0.0088 1.0000
13.250 1.4631 0.02778 0.02249 -0.0138 0.0085 1.0000
13.500 1.4658 0.02929 0.02409 -0.0117 0.0084 1.0000
13.750 1.4690 0.03086 0.02575 -0.0099 0.0082 1.0000
14.000 1.4721 0.03256 0.02753 -0.0085 0.0080 1.0000
14.250 1.4734 0.03451 0.02958 -0.0072 0.0079 1.0000
14.500 1.4713 0.03697 0.03214 -0.0063 0.0077 1.0000
14.750 1.4680 0.03974 0.03501 -0.0057 0.0076 1.0000
15.000 1.4628 0.04294 0.03833 -0.0056 0.0076 1.0000
15.250 1.4547 0.04672 0.04221 -0.0060 0.0074 1.0000
15.500 1.4438 0.05112 0.04673 -0.0069 0.0073 1.0000
15.750 1.4300 0.05619 0.05194 -0.0085 0.0072 1.0000
16.000 1.4148 0.06182 0.05770 -0.0105 0.0072 1.0000
16.250 1.4000 0.06770 0.06371 -0.0129 0.0072 1.0000
16.500 1.3855 0.07374 0.06988 -0.0156 0.0071 1.0000
16.750 1.3671 0.08054 0.07681 -0.0186 0.0071 1.0000
17.000 1.3502 0.08717 0.08357 -0.0216 0.0070 1.0000
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