GOE 693 AIRFOIL (goe693-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 693 AIRFOIL (goe693-il) Reynolds number: 50,000 Max Cl/Cd: 35.62 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe693-il-50000-n5.txt Download as CSV file: xf-goe693-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3805 0.10327 0.09580 -0.0433 1.0000 0.0855
-9.250 -0.3838 0.09997 0.09256 -0.0438 1.0000 0.0860
-9.000 -0.3899 0.09664 0.08932 -0.0443 1.0000 0.0863
-8.750 -0.3996 0.09330 0.08608 -0.0444 1.0000 0.0861
-8.500 -0.4144 0.08997 0.08288 -0.0442 1.0000 0.0855
-8.250 -0.4360 0.08662 0.07967 -0.0437 1.0000 0.0847
-8.000 -0.4584 0.08218 0.07533 -0.0446 1.0000 0.0836
-7.750 -0.4857 0.07635 0.06953 -0.0463 1.0000 0.0823
-7.500 -0.5094 0.07017 0.06325 -0.0475 1.0000 0.0814
-7.250 -0.5203 0.06573 0.05867 -0.0472 1.0000 0.0813
-7.000 -0.5233 0.06240 0.05522 -0.0462 1.0000 0.0817
-6.750 -0.5210 0.06000 0.05274 -0.0449 1.0000 0.0825
-6.500 -0.4966 0.05733 0.04990 -0.0476 0.9943 0.0851
-6.250 -0.4724 0.05302 0.04520 -0.0515 0.9871 0.0880
-6.000 -0.4474 0.04818 0.03979 -0.0553 0.9802 0.0901
-5.750 -0.4195 0.04373 0.03464 -0.0586 0.9739 0.0922
-5.500 -0.3918 0.04059 0.03092 -0.0606 0.9672 0.0951
-5.250 -0.3601 0.03936 0.02961 -0.0625 0.9613 0.0994
-5.000 -0.3307 0.03744 0.02728 -0.0640 0.9546 0.1043
-4.750 -0.2982 0.03514 0.02429 -0.0657 0.9486 0.1089
-4.500 -0.2656 0.03410 0.02325 -0.0674 0.9433 0.1144
-4.250 -0.2371 0.03299 0.02179 -0.0681 0.9359 0.1224
-4.000 -0.2023 0.03189 0.02056 -0.0700 0.9310 0.1298
-3.750 -0.1733 0.03110 0.01943 -0.0705 0.9240 0.1405
-3.500 -0.1419 0.03040 0.01877 -0.0717 0.9179 0.1503
-3.250 -0.1049 0.02972 0.01798 -0.0737 0.9138 0.1639
-3.000 -0.0801 0.02926 0.01741 -0.0735 0.9055 0.1758
-2.750 -0.0451 0.02878 0.01686 -0.0750 0.9006 0.1912
-2.500 -0.0153 0.02843 0.01645 -0.0757 0.8943 0.2067
-2.250 0.0155 0.02809 0.01606 -0.0765 0.8879 0.2230
-2.000 0.0526 0.02764 0.01565 -0.0784 0.8837 0.2438
-1.750 0.0766 0.02743 0.01547 -0.0780 0.8758 0.2637
-1.500 0.1102 0.02698 0.01516 -0.0793 0.8706 0.2958
-1.250 0.1392 0.02652 0.01499 -0.0799 0.8647 0.3479
-1.000 0.1636 0.02587 0.01495 -0.0795 0.8578 0.4582
-0.750 0.2178 0.02454 0.01501 -0.0826 0.8551 0.9869
-0.500 0.2450 0.02480 0.01498 -0.0828 0.8475 1.0000
-0.250 0.2745 0.02499 0.01492 -0.0833 0.8406 1.0000
0.000 0.3018 0.02522 0.01494 -0.0833 0.8334 1.0000
0.500 0.3574 0.02559 0.01497 -0.0834 0.8171 1.0000
0.750 0.3902 0.02554 0.01478 -0.0839 0.8084 1.0000
1.000 0.4153 0.02567 0.01479 -0.0832 0.7971 1.0000
1.250 0.4540 0.02541 0.01440 -0.0845 0.7902 1.0000
1.500 0.4747 0.02569 0.01462 -0.0832 0.7783 1.0000
1.750 0.5015 0.02584 0.01469 -0.0828 0.7691 1.0000
2.000 0.5311 0.02591 0.01470 -0.0828 0.7609 1.0000
2.250 0.5540 0.02622 0.01498 -0.0819 0.7508 1.0000
2.500 0.5864 0.02619 0.01490 -0.0823 0.7436 1.0000
2.750 0.6072 0.02658 0.01529 -0.0811 0.7324 1.0000
3.000 0.6416 0.02645 0.01513 -0.0816 0.7257 1.0000
3.250 0.6615 0.02687 0.01559 -0.0803 0.7138 1.0000
3.500 0.6854 0.02715 0.01589 -0.0795 0.7031 1.0000
3.750 0.7177 0.02706 0.01580 -0.0796 0.6949 1.0000
4.000 0.7382 0.02744 0.01623 -0.0783 0.6821 1.0000
4.250 0.7619 0.02766 0.01649 -0.0773 0.6699 1.0000
4.500 0.7895 0.02766 0.01653 -0.0767 0.6583 1.0000
4.750 0.8193 0.02750 0.01642 -0.0763 0.6466 1.0000
5.000 0.8416 0.02766 0.01662 -0.0749 0.6317 1.0000
5.250 0.8644 0.02776 0.01678 -0.0736 0.6165 1.0000
5.500 0.8871 0.02787 0.01696 -0.0723 0.6010 1.0000
5.750 0.9096 0.02799 0.01714 -0.0710 0.5853 1.0000
6.000 0.9322 0.02810 0.01731 -0.0696 0.5690 1.0000
6.250 0.9546 0.02823 0.01750 -0.0683 0.5526 1.0000
6.500 0.9755 0.02846 0.01778 -0.0668 0.5356 1.0000
6.750 0.9953 0.02879 0.01819 -0.0653 0.5185 1.0000
7.000 1.0158 0.02914 0.01861 -0.0638 0.5019 1.0000
7.250 1.0362 0.02950 0.01905 -0.0624 0.4851 1.0000
7.500 1.0567 0.02989 0.01949 -0.0610 0.4684 1.0000
7.750 1.0772 0.03033 0.01998 -0.0596 0.4519 1.0000
8.000 1.0966 0.03081 0.02048 -0.0581 0.4343 1.0000
8.250 1.1153 0.03131 0.02100 -0.0564 0.4156 1.0000
8.500 1.1329 0.03190 0.02155 -0.0547 0.3966 1.0000
8.750 1.1459 0.03274 0.02243 -0.0525 0.3770 1.0000
9.000 1.1582 0.03361 0.02332 -0.0503 0.3579 1.0000
9.250 1.1687 0.03455 0.02426 -0.0479 0.3395 1.0000
9.500 1.1790 0.03558 0.02533 -0.0455 0.3222 1.0000
9.750 1.1896 0.03670 0.02651 -0.0434 0.3064 1.0000
10.000 1.1999 0.03789 0.02779 -0.0414 0.2917 1.0000
10.250 1.2106 0.03914 0.02914 -0.0395 0.2782 1.0000
10.500 1.2210 0.04043 0.03053 -0.0377 0.2655 1.0000
10.750 1.2302 0.04176 0.03198 -0.0358 0.2533 1.0000
11.000 1.2384 0.04315 0.03342 -0.0339 0.2415 1.0000
11.250 1.2434 0.04477 0.03518 -0.0320 0.2294 1.0000
11.500 1.2450 0.04658 0.03707 -0.0301 0.2167 1.0000
11.750 1.2430 0.04862 0.03913 -0.0281 0.2034 1.0000
12.000 1.2387 0.05092 0.04142 -0.0265 0.1897 1.0000
12.250 1.2337 0.05351 0.04399 -0.0251 0.1762 1.0000
12.500 1.2294 0.05626 0.04677 -0.0240 0.1636 1.0000
12.750 1.2262 0.05906 0.04962 -0.0230 0.1524 1.0000
13.000 1.2213 0.06217 0.05284 -0.0224 0.1415 1.0000
13.250 1.2146 0.06576 0.05666 -0.0221 0.1306 1.0000
13.500 1.2074 0.06949 0.06057 -0.0221 0.1202 1.0000
13.750 1.1999 0.07337 0.06455 -0.0223 0.1108 1.0000
14.000 1.1918 0.07739 0.06861 -0.0228 0.1025 1.0000
14.250 1.1837 0.08175 0.07306 -0.0234 0.0943 1.0000
14.500 1.1760 0.08602 0.07729 -0.0241 0.0879 1.0000
14.750 1.1688 0.09045 0.08179 -0.0248 0.0817 1.0000
15.000 1.1631 0.09462 0.08591 -0.0255 0.0768 1.0000
15.250 1.1552 0.09966 0.09120 -0.0268 0.0719 1.0000
15.500 1.1501 0.10400 0.09556 -0.0279 0.0679 1.0000
15.750 1.1448 0.10862 0.10027 -0.0291 0.0648 1.0000
16.000 1.1347 0.11465 0.10658 -0.0314 0.0623 1.0000
16.250 1.1248 0.12074 0.11289 -0.0339 0.0602 1.0000
16.500 1.1165 0.12657 0.11885 -0.0365 0.0583 1.0000
16.750 1.1204 0.12930 0.12150 -0.0373 0.0558 1.0000
17.000 1.1010 0.13842 0.13089 -0.0422 0.0551 1.0000
17.250 1.0757 0.14976 0.14246 -0.0488 0.0548 1.0000
17.500 1.0429 0.16455 0.15737 -0.0575 0.0549 1.0000
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