GOE 507 AIRFOIL (goe507-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 507 AIRFOIL (goe507-il) Reynolds number: 500,000 Max Cl/Cd: 82.01 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe507-il-500000-n5.txt Download as CSV file: xf-goe507-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 507 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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6340 0.09110 0.08855 -0.0339 1.0000 0.0110
-12.250 -0.6600 0.08274 0.08017 -0.0387 1.0000 0.0110
-12.000 -0.8992 0.03833 0.03524 -0.0684 1.0000 0.0088
-11.750 -0.9082 0.03218 0.02872 -0.0688 1.0000 0.0088
-11.500 -0.9043 0.02940 0.02571 -0.0675 1.0000 0.0090
-11.250 -0.8977 0.02724 0.02337 -0.0659 1.0000 0.0093
-11.000 -0.8885 0.02559 0.02158 -0.0640 1.0000 0.0096
-10.750 -0.8636 0.02386 0.01965 -0.0652 0.9967 0.0100
-10.500 -0.8372 0.02238 0.01797 -0.0663 0.9924 0.0105
-10.250 -0.8100 0.02108 0.01646 -0.0673 0.9882 0.0110
-10.000 -0.7816 0.01988 0.01508 -0.0684 0.9849 0.0115
-9.750 -0.7549 0.01871 0.01376 -0.0691 0.9803 0.0123
-9.500 -0.7251 0.01774 0.01264 -0.0702 0.9771 0.0130
-9.250 -0.6965 0.01693 0.01167 -0.0709 0.9726 0.0141
-9.000 -0.6672 0.01607 0.01069 -0.0717 0.9684 0.0151
-8.750 -0.6376 0.01530 0.00981 -0.0725 0.9645 0.0167
-8.500 -0.6090 0.01466 0.00903 -0.0730 0.9594 0.0183
-8.250 -0.5791 0.01399 0.00830 -0.0738 0.9554 0.0209
-8.000 -0.5510 0.01350 0.00776 -0.0740 0.9494 0.0240
-7.750 -0.5210 0.01326 0.00753 -0.0746 0.9444 0.0284
-7.500 -0.4920 0.01316 0.00742 -0.0748 0.9387 0.0321
-7.250 -0.4626 0.01321 0.00745 -0.0750 0.9332 0.0356
-7.000 -0.4339 0.01315 0.00731 -0.0751 0.9280 0.0385
-6.750 -0.4062 0.01312 0.00719 -0.0750 0.9217 0.0400
-6.500 -0.3789 0.01286 0.00684 -0.0749 0.9161 0.0415
-6.250 -0.3527 0.01265 0.00661 -0.0746 0.9099 0.0434
-6.000 -0.3256 0.01255 0.00646 -0.0744 0.9042 0.0451
-5.750 -0.2984 0.01243 0.00628 -0.0742 0.8993 0.0469
-5.500 -0.2719 0.01225 0.00604 -0.0739 0.8931 0.0486
-5.250 -0.2451 0.01208 0.00578 -0.0736 0.8866 0.0502
-5.000 -0.2187 0.01187 0.00548 -0.0732 0.8795 0.0512
-4.750 -0.1923 0.01165 0.00518 -0.0728 0.8724 0.0519
-4.500 -0.1658 0.01141 0.00488 -0.0725 0.8657 0.0524
-4.250 -0.1395 0.01114 0.00454 -0.0721 0.8586 0.0527
-4.000 -0.1131 0.01088 0.00422 -0.0717 0.8523 0.0529
-3.750 -0.0868 0.01063 0.00392 -0.0713 0.8447 0.0531
-3.500 -0.0606 0.01032 0.00354 -0.0708 0.8381 0.0536
-3.250 -0.0350 0.00992 0.00311 -0.0704 0.8312 0.0552
-3.000 -0.0086 0.00966 0.00282 -0.0700 0.8254 0.0562
-2.750 0.0180 0.00945 0.00259 -0.0697 0.8194 0.0574
-2.500 0.0448 0.00927 0.00239 -0.0693 0.8130 0.0585
-2.250 0.0716 0.00913 0.00221 -0.0690 0.8070 0.0597
-2.000 0.0986 0.00900 0.00207 -0.0687 0.8002 0.0609
-1.750 0.1255 0.00889 0.00192 -0.0684 0.7935 0.0621
-1.500 0.1526 0.00879 0.00181 -0.0682 0.7865 0.0632
-1.250 0.1796 0.00871 0.00170 -0.0678 0.7790 0.0642
-1.000 0.2067 0.00864 0.00161 -0.0676 0.7715 0.0651
-0.750 0.2336 0.00857 0.00152 -0.0673 0.7633 0.0661
-0.500 0.2606 0.00850 0.00144 -0.0669 0.7545 0.0687
-0.250 0.2873 0.00844 0.00138 -0.0666 0.7451 0.0722
0.000 0.3137 0.00839 0.00132 -0.0661 0.7313 0.0777
0.250 0.3386 0.00816 0.00129 -0.0655 0.7136 0.1492
0.500 0.3642 0.00812 0.00128 -0.0650 0.6914 0.1796
0.750 0.3894 0.00813 0.00128 -0.0643 0.6649 0.2048
1.000 0.4141 0.00817 0.00128 -0.0636 0.6325 0.2264
1.500 0.4604 0.00836 0.00137 -0.0617 0.5505 0.3070
1.750 0.4802 0.00791 0.00148 -0.0603 0.5242 0.5438
2.000 0.5317 0.00711 0.00174 -0.0653 0.4985 0.9764
2.250 0.5745 0.00732 0.00185 -0.0686 0.4736 0.9940
2.500 0.6086 0.00754 0.00196 -0.0701 0.4489 1.0000
2.750 0.6317 0.00774 0.00206 -0.0691 0.4253 1.0000
3.000 0.6541 0.00799 0.00218 -0.0680 0.3969 1.0000
3.250 0.6766 0.00825 0.00233 -0.0669 0.3694 1.0000
3.500 0.6985 0.00855 0.00249 -0.0658 0.3373 1.0000
3.750 0.7203 0.00888 0.00267 -0.0646 0.3046 1.0000
4.000 0.7417 0.00925 0.00289 -0.0634 0.2698 1.0000
4.250 0.7633 0.00961 0.00311 -0.0622 0.2398 1.0000
4.500 0.7852 0.00996 0.00335 -0.0611 0.2139 1.0000
4.750 0.8065 0.01036 0.00362 -0.0599 0.1828 1.0000
5.000 0.8217 0.01131 0.00410 -0.0579 0.0954 1.0000
5.250 0.8429 0.01176 0.00446 -0.0567 0.0774 1.0000
5.500 0.8652 0.01211 0.00478 -0.0557 0.0696 1.0000
5.750 0.8879 0.01243 0.00509 -0.0547 0.0646 1.0000
6.000 0.9102 0.01279 0.00544 -0.0537 0.0603 1.0000
6.250 0.9334 0.01306 0.00575 -0.0529 0.0580 1.0000
6.500 0.9566 0.01333 0.00605 -0.0520 0.0552 1.0000
6.750 0.9791 0.01365 0.00639 -0.0511 0.0518 1.0000
7.000 1.0007 0.01406 0.00680 -0.0500 0.0475 1.0000
7.250 1.0241 0.01429 0.00709 -0.0493 0.0454 1.0000
7.500 1.0469 0.01458 0.00741 -0.0484 0.0402 1.0000
7.750 1.0682 0.01498 0.00776 -0.0474 0.0326 1.0000
8.000 1.0888 0.01544 0.00817 -0.0462 0.0264 1.0000
8.250 1.1091 0.01592 0.00867 -0.0450 0.0227 1.0000
8.500 1.1284 0.01645 0.00920 -0.0437 0.0199 1.0000
8.750 1.1474 0.01699 0.00978 -0.0423 0.0178 1.0000
9.000 1.1661 0.01753 0.01036 -0.0409 0.0162 1.0000
9.250 1.1829 0.01820 0.01105 -0.0392 0.0148 1.0000
9.500 1.2006 0.01876 0.01168 -0.0377 0.0140 1.0000
9.750 1.2172 0.01935 0.01234 -0.0360 0.0130 1.0000
10.000 1.2316 0.01997 0.01301 -0.0339 0.0123 1.0000
10.250 1.2426 0.02076 0.01383 -0.0314 0.0116 1.0000
10.500 1.2557 0.02142 0.01457 -0.0292 0.0111 1.0000
10.750 1.2683 0.02213 0.01536 -0.0271 0.0105 1.0000
11.000 1.2798 0.02293 0.01624 -0.0249 0.0101 1.0000
11.250 1.2908 0.02378 0.01717 -0.0228 0.0097 1.0000
11.500 1.3000 0.02477 0.01822 -0.0206 0.0094 1.0000
11.750 1.3063 0.02600 0.01952 -0.0183 0.0090 1.0000
12.000 1.3154 0.02709 0.02072 -0.0164 0.0087 1.0000
12.250 1.3235 0.02826 0.02200 -0.0145 0.0085 1.0000
12.500 1.3306 0.02956 0.02340 -0.0127 0.0082 1.0000
12.750 1.3375 0.03092 0.02486 -0.0111 0.0080 1.0000
13.000 1.3428 0.03247 0.02651 -0.0095 0.0077 1.0000
13.250 1.3488 0.03400 0.02815 -0.0082 0.0075 1.0000
13.500 1.3529 0.03578 0.03001 -0.0070 0.0073 1.0000
13.750 1.3539 0.03791 0.03224 -0.0058 0.0072 1.0000
14.000 1.3514 0.04049 0.03492 -0.0048 0.0070 1.0000
14.250 1.3516 0.04294 0.03750 -0.0041 0.0069 1.0000
14.500 1.3521 0.04546 0.04017 -0.0037 0.0068 1.0000
14.750 1.3487 0.04855 0.04340 -0.0035 0.0067 1.0000
15.000 1.3465 0.05165 0.04665 -0.0037 0.0065 1.0000
15.250 1.3407 0.05539 0.05052 -0.0042 0.0065 1.0000
15.500 1.3360 0.05918 0.05446 -0.0051 0.0064 1.0000
15.750 1.3285 0.06360 0.05903 -0.0064 0.0062 1.0000
16.000 1.3214 0.06816 0.06373 -0.0081 0.0062 1.0000
16.250 1.3120 0.07331 0.06902 -0.0102 0.0061 1.0000
16.500 1.3007 0.07890 0.07476 -0.0126 0.0061 1.0000
16.750 1.2878 0.08504 0.08105 -0.0154 0.0060 1.0000
17.000 1.2755 0.09128 0.08742 -0.0185 0.0060 1.0000
17.250 1.2605 0.09818 0.09448 -0.0220 0.0060 1.0000
17.500 1.2462 0.10524 0.10168 -0.0257 0.0059 1.0000
17.750 1.2296 0.11297 0.10955 -0.0299 0.0059 1.0000
18.000 1.2113 0.12124 0.11797 -0.0344 0.0059 1.0000
18.250 1.1944 0.12949 0.12636 -0.0391 0.0059 1.0000
18.500 1.1744 0.13874 0.13576 -0.0443 0.0059 1.0000
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