GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 693 AIRFOIL (goe693-il) Reynolds number: 100,000 Max Cl/Cd: 55.66 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe693-il-100000-n5.txt Download as CSV file: xf-goe693-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 693 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4077 0.09369 0.08841 -0.0468 1.0000 0.0517
-9.500 -0.4115 0.09038 0.08516 -0.0475 1.0000 0.0526
-9.250 -0.4207 0.08672 0.08157 -0.0480 1.0000 0.0532
-9.000 -0.4364 0.08286 0.07780 -0.0482 1.0000 0.0535
-8.750 -0.4615 0.07911 0.07418 -0.0475 1.0000 0.0534
-8.500 -0.4944 0.07482 0.07000 -0.0470 1.0000 0.0530
-8.250 -0.5160 0.06674 0.06189 -0.0524 0.9964 0.0530
-8.000 -0.5231 0.05190 0.04650 -0.0650 0.9852 0.0535
-7.750 -0.5154 0.04340 0.03731 -0.0702 0.9761 0.0549
-7.500 -0.4988 0.03731 0.03036 -0.0732 0.9688 0.0574
-7.250 -0.4749 0.03329 0.02561 -0.0751 0.9623 0.0589
-7.000 -0.4439 0.03163 0.02380 -0.0769 0.9575 0.0602
-6.750 -0.4154 0.03022 0.02219 -0.0779 0.9505 0.0617
-6.500 -0.3815 0.02882 0.02053 -0.0799 0.9463 0.0642
-6.250 -0.3534 0.02736 0.01872 -0.0806 0.9391 0.0672
-6.000 -0.3222 0.02583 0.01684 -0.0817 0.9332 0.0698
-5.750 -0.2876 0.02490 0.01586 -0.0834 0.9293 0.0721
-5.500 -0.2618 0.02415 0.01500 -0.0832 0.9202 0.0749
-5.250 -0.2285 0.02320 0.01382 -0.0844 0.9153 0.0794
-5.000 -0.2008 0.02257 0.01313 -0.0846 0.9073 0.0837
-4.750 -0.1694 0.02199 0.01247 -0.0854 0.9012 0.0895
-4.500 -0.1394 0.02128 0.01162 -0.0858 0.8949 0.0956
-4.250 -0.1108 0.02081 0.01114 -0.0861 0.8876 0.1025
-4.000 -0.0780 0.02023 0.01047 -0.0870 0.8830 0.1117
-3.750 -0.0523 0.01989 0.01010 -0.0867 0.8741 0.1206
-3.500 -0.0211 0.01941 0.00960 -0.0873 0.8690 0.1305
-3.250 0.0060 0.01914 0.00923 -0.0872 0.8612 0.1409
-3.000 0.0355 0.01874 0.00888 -0.0875 0.8553 0.1512
-2.750 0.0637 0.01842 0.00855 -0.0876 0.8488 0.1619
-2.500 0.0917 0.01814 0.00826 -0.0876 0.8419 0.1735
-2.250 0.1224 0.01779 0.00790 -0.0880 0.8373 0.1866
-2.000 0.1476 0.01758 0.00775 -0.0876 0.8291 0.1995
-1.750 0.1769 0.01727 0.00749 -0.0878 0.8237 0.2176
-1.500 0.2038 0.01702 0.00733 -0.0876 0.8170 0.2407
-1.250 0.2313 0.01673 0.00718 -0.0876 0.8106 0.2772
-1.000 0.2606 0.01627 0.00697 -0.0878 0.8057 0.3491
-0.750 0.2836 0.01575 0.00701 -0.0870 0.7973 0.4898
-0.500 0.3064 0.01492 0.00698 -0.0850 0.7911 0.7248
-0.250 0.3614 0.01460 0.00698 -0.0893 0.7822 0.9485
0.000 0.4105 0.01448 0.00667 -0.0933 0.7733 1.0000
0.250 0.4340 0.01453 0.00659 -0.0923 0.7622 1.0000
0.500 0.4588 0.01459 0.00653 -0.0916 0.7531 1.0000
0.750 0.4843 0.01467 0.00649 -0.0910 0.7453 1.0000
1.000 0.5095 0.01478 0.00652 -0.0904 0.7380 1.0000
1.250 0.5347 0.01490 0.00655 -0.0898 0.7302 1.0000
1.500 0.5606 0.01501 0.00659 -0.0893 0.7228 1.0000
1.750 0.5856 0.01513 0.00665 -0.0887 0.7140 1.0000
2.000 0.6108 0.01524 0.00670 -0.0881 0.7049 1.0000
2.250 0.6368 0.01532 0.00671 -0.0875 0.6955 1.0000
2.500 0.6609 0.01546 0.00683 -0.0867 0.6844 1.0000
2.750 0.6864 0.01555 0.00687 -0.0860 0.6741 1.0000
3.000 0.7118 0.01566 0.00694 -0.0854 0.6636 1.0000
3.250 0.7361 0.01582 0.00711 -0.0846 0.6527 1.0000
3.500 0.7615 0.01595 0.00723 -0.0840 0.6426 1.0000
3.750 0.7867 0.01608 0.00734 -0.0834 0.6314 1.0000
4.000 0.8107 0.01624 0.00752 -0.0825 0.6182 1.0000
4.250 0.8348 0.01639 0.00769 -0.0817 0.6046 1.0000
4.500 0.8591 0.01656 0.00786 -0.0810 0.5909 1.0000
4.750 0.8831 0.01673 0.00805 -0.0801 0.5765 1.0000
5.000 0.9066 0.01691 0.00824 -0.0792 0.5597 1.0000
5.250 0.9295 0.01711 0.00842 -0.0782 0.5409 1.0000
5.500 0.9525 0.01733 0.00861 -0.0771 0.5223 1.0000
5.750 0.9748 0.01759 0.00885 -0.0760 0.5019 1.0000
6.000 0.9964 0.01790 0.00912 -0.0748 0.4797 1.0000
6.500 1.0383 0.01866 0.00975 -0.0723 0.4383 1.0000
6.750 1.0583 0.01911 0.01016 -0.0709 0.4184 1.0000
7.000 1.0778 0.01962 0.01060 -0.0695 0.3995 1.0000
7.250 1.0967 0.02016 0.01108 -0.0681 0.3818 1.0000
7.500 1.1153 0.02072 0.01162 -0.0666 0.3646 1.0000
7.750 1.1334 0.02130 0.01221 -0.0651 0.3481 1.0000
8.000 1.1508 0.02191 0.01282 -0.0635 0.3320 1.0000
8.250 1.1677 0.02254 0.01346 -0.0618 0.3163 1.0000
8.500 1.1837 0.02320 0.01414 -0.0601 0.3004 1.0000
8.750 1.1991 0.02386 0.01486 -0.0582 0.2847 1.0000
9.000 1.2133 0.02455 0.01563 -0.0562 0.2690 1.0000
9.250 1.2254 0.02527 0.01639 -0.0539 0.2534 1.0000
9.500 1.2367 0.02607 0.01722 -0.0516 0.2384 1.0000
9.750 1.2465 0.02698 0.01812 -0.0492 0.2229 1.0000
10.000 1.2542 0.02803 0.01913 -0.0467 0.2068 1.0000
10.250 1.2599 0.02927 0.02031 -0.0442 0.1914 1.0000
10.500 1.2646 0.03066 0.02162 -0.0418 0.1767 1.0000
10.750 1.2699 0.03210 0.02305 -0.0397 0.1633 1.0000
11.000 1.2757 0.03358 0.02453 -0.0377 0.1518 1.0000
11.250 1.2821 0.03506 0.02608 -0.0360 0.1408 1.0000
11.500 1.2917 0.03637 0.02755 -0.0346 0.1281 1.0000
11.750 1.2993 0.03787 0.02914 -0.0333 0.1136 1.0000
12.000 1.3035 0.03970 0.03100 -0.0319 0.0983 1.0000
12.250 1.3030 0.04202 0.03326 -0.0305 0.0866 1.0000
12.500 1.2999 0.04468 0.03589 -0.0291 0.0770 1.0000
12.750 1.2979 0.04737 0.03865 -0.0279 0.0666 1.0000
13.000 1.2966 0.05009 0.04145 -0.0269 0.0566 1.0000
13.250 1.2937 0.05305 0.04447 -0.0261 0.0496 1.0000
13.500 1.2887 0.05634 0.04780 -0.0255 0.0454 1.0000
13.750 1.2837 0.05973 0.05128 -0.0251 0.0424 1.0000
14.000 1.2767 0.06349 0.05512 -0.0249 0.0402 1.0000
14.250 1.2692 0.06746 0.05918 -0.0250 0.0385 1.0000
14.500 1.2632 0.07137 0.06326 -0.0253 0.0368 1.0000
14.750 1.2563 0.07555 0.06757 -0.0258 0.0353 1.0000
15.000 1.2482 0.08003 0.07217 -0.0266 0.0341 1.0000
15.250 1.2390 0.08480 0.07704 -0.0277 0.0332 1.0000
15.500 1.2305 0.08954 0.08187 -0.0288 0.0323 1.0000
15.750 1.2252 0.09394 0.08644 -0.0299 0.0313 1.0000
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