GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 167 (V.KARMAN PROP.2) AIRFOIL (goe167-il) Reynolds number: 100,000 Max Cl/Cd: 58.78 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe167-il-100000-n5.txt Download as CSV file: xf-goe167-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 167 (V.KARMAN PROP.2) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3378 0.09517 0.09067 -0.0245 1.0000 0.0495
-7.750 -0.3366 0.09220 0.08777 -0.0265 1.0000 0.0512
-7.500 -0.3358 0.08925 0.08491 -0.0320 1.0000 0.0533
-7.250 -0.3298 0.08584 0.08151 -0.0410 1.0000 0.0543
-7.000 -0.3131 0.08155 0.07712 -0.0492 0.9898 0.0546
-6.750 -0.3016 0.07633 0.07205 -0.0451 0.9761 0.0566
-6.500 -0.2797 0.07273 0.06841 -0.0473 0.9544 0.0600
-6.250 -0.2545 0.06831 0.06387 -0.0537 0.9270 0.0638
-6.000 -0.2159 0.06326 0.05824 -0.0677 0.8949 0.0681
-5.750 -0.2028 0.05871 0.05381 -0.0664 0.8669 0.0696
-5.500 -0.1864 0.05615 0.05117 -0.0657 0.8387 0.0735
-5.250 -0.1542 0.05252 0.04690 -0.0720 0.8145 0.0823
-5.000 -0.1371 0.04911 0.04344 -0.0717 0.7915 0.0838
-4.500 -0.0831 0.04138 0.03490 -0.0747 0.7533 0.0638
-4.000 -0.0221 0.03451 0.02683 -0.0771 0.7215 0.0534
-3.750 0.0050 0.03215 0.02412 -0.0777 0.7075 0.0526
-3.500 0.0332 0.03007 0.02164 -0.0781 0.6951 0.0520
-3.250 0.0626 0.02843 0.01952 -0.0785 0.6834 0.0531
-3.000 0.0918 0.02706 0.01772 -0.0787 0.6729 0.0539
-2.750 0.1203 0.02557 0.01587 -0.0789 0.6639 0.0536
-2.500 0.1493 0.02429 0.01428 -0.0792 0.6545 0.0533
-2.250 0.1781 0.02320 0.01287 -0.0792 0.6472 0.0532
-2.000 0.2071 0.02224 0.01167 -0.0794 0.6396 0.0533
-1.750 0.2356 0.02144 0.01061 -0.0793 0.6335 0.0536
-1.500 0.2643 0.02072 0.00974 -0.0794 0.6265 0.0540
-1.250 0.2924 0.02004 0.00893 -0.0794 0.6207 0.0557
-1.000 0.3204 0.01951 0.00839 -0.0796 0.6149 0.0585
-0.750 0.3484 0.01906 0.00791 -0.0796 0.6093 0.0601
-0.500 0.3762 0.01867 0.00745 -0.0795 0.6049 0.0611
-0.250 0.4042 0.01836 0.00710 -0.0796 0.6002 0.0625
0.000 0.4324 0.01814 0.00681 -0.0797 0.5953 0.0643
0.250 0.4605 0.01801 0.00656 -0.0797 0.5910 0.0667
0.500 0.4888 0.01791 0.00639 -0.0798 0.5870 0.0706
0.750 0.5175 0.01787 0.00633 -0.0800 0.5824 0.0783
1.000 0.5464 0.01777 0.00629 -0.0803 0.5786 0.1103
1.250 0.5699 0.01560 0.00623 -0.0793 0.5754 1.0000
1.500 0.5983 0.01585 0.00629 -0.0794 0.5720 1.0000
1.750 0.6267 0.01608 0.00644 -0.0796 0.5675 1.0000
2.000 0.6548 0.01632 0.00658 -0.0798 0.5629 1.0000
2.250 0.6828 0.01656 0.00669 -0.0798 0.5589 1.0000
2.500 0.7107 0.01681 0.00692 -0.0800 0.5538 1.0000
2.750 0.7386 0.01705 0.00714 -0.0802 0.5486 1.0000
3.000 0.7664 0.01729 0.00729 -0.0802 0.5442 1.0000
3.250 0.7940 0.01756 0.00758 -0.0803 0.5392 1.0000
3.500 0.8216 0.01783 0.00789 -0.0805 0.5342 1.0000
3.750 0.8493 0.01809 0.00813 -0.0805 0.5300 1.0000
4.000 0.8768 0.01836 0.00842 -0.0806 0.5254 1.0000
4.250 0.9039 0.01864 0.00880 -0.0807 0.5195 1.0000
4.500 0.9312 0.01885 0.00900 -0.0806 0.5139 1.0000
4.750 0.9577 0.01908 0.00931 -0.0806 0.5060 1.0000
5.000 0.9845 0.01916 0.00938 -0.0803 0.4974 1.0000
5.250 1.0103 0.01931 0.00966 -0.0801 0.4866 1.0000
5.500 1.0365 0.01945 0.00986 -0.0798 0.4769 1.0000
5.750 1.0628 0.01962 0.01012 -0.0796 0.4689 1.0000
6.000 1.0889 0.01988 0.01056 -0.0795 0.4616 1.0000
6.250 1.1149 0.02010 0.01089 -0.0793 0.4540 1.0000
6.500 1.1404 0.02033 0.01130 -0.0791 0.4443 1.0000
6.750 1.1657 0.02051 0.01163 -0.0788 0.4337 1.0000
7.000 1.1909 0.02072 0.01200 -0.0784 0.4230 1.0000
7.250 1.2155 0.02098 0.01246 -0.0781 0.4098 1.0000
7.500 1.2387 0.02117 0.01278 -0.0774 0.3863 1.0000
7.750 1.2596 0.02143 0.01300 -0.0764 0.3427 1.0000
8.000 1.2757 0.02218 0.01341 -0.0749 0.2866 1.0000
8.500 1.3010 0.02477 0.01562 -0.0716 0.2189 1.0000
8.750 1.3119 0.02619 0.01696 -0.0698 0.1793 1.0000
9.000 1.3068 0.02876 0.01896 -0.0666 0.0977 1.0000
9.250 1.3073 0.03070 0.02084 -0.0637 0.0813 1.0000
9.500 1.3058 0.03253 0.02269 -0.0606 0.0719 1.0000
9.750 1.3038 0.03456 0.02479 -0.0578 0.0624 1.0000
10.000 1.3045 0.03663 0.02698 -0.0559 0.0535 1.0000
10.500 1.3051 0.04148 0.03211 -0.0534 0.0390 1.0000
10.750 1.3048 0.04425 0.03500 -0.0527 0.0339 1.0000
11.000 1.3037 0.04724 0.03806 -0.0523 0.0303 1.0000
11.250 1.3018 0.05043 0.04135 -0.0520 0.0279 1.0000
11.500 1.2995 0.05375 0.04477 -0.0520 0.0260 1.0000
11.750 1.2954 0.05733 0.04842 -0.0521 0.0245 1.0000
12.000 1.2901 0.06114 0.05235 -0.0522 0.0236 1.0000
12.250 1.2850 0.06492 0.05629 -0.0523 0.0229 1.0000
12.500 1.2799 0.06874 0.06026 -0.0525 0.0224 1.0000
12.750 1.2749 0.07253 0.06419 -0.0526 0.0219 1.0000
13.000 1.2704 0.07623 0.06803 -0.0527 0.0214 1.0000
13.250 1.2671 0.07983 0.07175 -0.0528 0.0209 1.0000
13.500 1.2652 0.08325 0.07529 -0.0528 0.0205 1.0000
13.750 1.2643 0.08654 0.07868 -0.0528 0.0199 1.0000
14.000 1.2641 0.08971 0.08193 -0.0527 0.0193 1.0000
14.250 1.2649 0.09267 0.08494 -0.0525 0.0186 1.0000
14.500 1.2683 0.09509 0.08741 -0.0515 0.0179 1.0000
14.750 1.2719 0.09787 0.09037 -0.0513 0.0174 1.0000
15.000 1.2751 0.10077 0.09350 -0.0510 0.0171 1.0000
15.250 1.2775 0.10388 0.09680 -0.0509 0.0168 1.0000
15.500 1.2781 0.10742 0.10055 -0.0511 0.0166 1.0000
15.750 1.2764 0.11148 0.10483 -0.0519 0.0164 1.0000
16.000 1.2724 0.11606 0.10962 -0.0531 0.0163 1.0000
16.250 1.2661 0.12122 0.11502 -0.0550 0.0162 1.0000
16.500 1.2575 0.12703 0.12106 -0.0575 0.0161 1.0000
16.750 1.2470 0.13348 0.12774 -0.0607 0.0161 1.0000
17.000 1.2349 0.14059 0.13509 -0.0646 0.0161 1.0000
17.250 1.2210 0.14852 0.14324 -0.0694 0.0162 1.0000
17.500 1.2052 0.15744 0.15237 -0.0751 0.0163 1.0000
17.750 1.1876 0.16763 0.16275 -0.0818 0.0164 1.0000
18.000 1.1673 0.17967 0.17497 -0.0898 0.0167 1.0000
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Polar data table (+)
Polar graphs
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