GOE 623 AIRFOIL (goe623-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 623 AIRFOIL (goe623-il) Reynolds number: 200,000 Max Cl/Cd: 75.38 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe623-il-200000.txt Download as CSV file: xf-goe623-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 623 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4063 0.08806 0.08481 -0.0468 1.0000 0.0732
-8.500 -0.4382 0.08596 0.08282 -0.0454 1.0000 0.0733
-8.250 -0.4690 0.08355 0.08043 -0.0439 1.0000 0.0734
-8.000 -0.4732 0.07898 0.07593 -0.0420 0.9992 0.0742
-7.750 -0.4495 0.07744 0.07443 -0.0390 0.9974 0.0755
-7.500 -0.4243 0.07445 0.07140 -0.0413 0.9940 0.0777
-7.000 -0.4150 0.04184 0.03723 -0.0717 0.9732 0.0628
-6.750 -0.3989 0.03181 0.02601 -0.0736 0.9670 0.0524
-6.500 -0.3699 0.02821 0.02202 -0.0753 0.9617 0.0531
-6.250 -0.3328 0.02611 0.01975 -0.0780 0.9585 0.0548
-6.000 -0.2984 0.02400 0.01730 -0.0797 0.9539 0.0555
-5.750 -0.2640 0.02238 0.01542 -0.0812 0.9483 0.0567
-5.500 -0.2249 0.02109 0.01388 -0.0834 0.9447 0.0591
-5.250 -0.1863 0.01982 0.01237 -0.0854 0.9412 0.0607
-5.000 -0.1564 0.01894 0.01132 -0.0856 0.9329 0.0618
-4.750 -0.1210 0.01746 0.00983 -0.0870 0.9282 0.0646
-4.500 -0.0921 0.01679 0.00916 -0.0871 0.9196 0.0679
-4.250 -0.0598 0.01606 0.00836 -0.0876 0.9131 0.0712
-4.000 -0.0328 0.01538 0.00764 -0.0871 0.9037 0.0748
-3.750 -0.0036 0.01467 0.00697 -0.0871 0.8961 0.0816
-3.500 0.0214 0.01413 0.00648 -0.0862 0.8850 0.0941
-3.250 0.0486 0.01363 0.00616 -0.0857 0.8757 0.1428
-3.000 0.0751 0.01331 0.00590 -0.0852 0.8655 0.1794
-2.750 0.1010 0.01310 0.00570 -0.0846 0.8542 0.2028
-2.500 0.1276 0.01285 0.00547 -0.0841 0.8441 0.2253
-2.250 0.1540 0.01262 0.00527 -0.0836 0.8331 0.2515
-2.000 0.1797 0.01236 0.00512 -0.0830 0.8212 0.2830
-1.750 0.2052 0.01196 0.00496 -0.0825 0.8107 0.3464
-1.500 0.2274 0.01117 0.00484 -0.0814 0.8004 0.5202
-1.250 0.2427 0.01034 0.00497 -0.0778 0.7889 0.7838
-1.000 0.2866 0.01019 0.00498 -0.0795 0.7798 0.9477
-0.750 0.3491 0.01018 0.00479 -0.0862 0.7700 0.9946
-0.500 0.3828 0.01020 0.00467 -0.0875 0.7587 1.0000
-0.250 0.4074 0.01023 0.00455 -0.0868 0.7482 1.0000
0.000 0.4321 0.01025 0.00441 -0.0860 0.7371 1.0000
0.250 0.4564 0.01029 0.00435 -0.0853 0.7248 1.0000
0.500 0.4812 0.01036 0.00430 -0.0846 0.7136 1.0000
0.750 0.5063 0.01042 0.00423 -0.0839 0.7033 1.0000
1.000 0.5311 0.01049 0.00419 -0.0831 0.6918 1.0000
1.250 0.5559 0.01058 0.00419 -0.0824 0.6798 1.0000
1.500 0.5811 0.01069 0.00419 -0.0818 0.6688 1.0000
1.750 0.6069 0.01082 0.00419 -0.0812 0.6590 1.0000
2.000 0.6321 0.01095 0.00428 -0.0806 0.6484 1.0000
2.250 0.6579 0.01110 0.00435 -0.0801 0.6390 1.0000
2.500 0.6838 0.01125 0.00443 -0.0797 0.6294 1.0000
2.750 0.7094 0.01141 0.00456 -0.0792 0.6193 1.0000
3.000 0.7356 0.01159 0.00465 -0.0788 0.6102 1.0000
3.250 0.7612 0.01174 0.00481 -0.0783 0.6000 1.0000
3.500 0.7870 0.01191 0.00495 -0.0779 0.5900 1.0000
3.750 0.8131 0.01209 0.00504 -0.0775 0.5799 1.0000
4.000 0.8382 0.01223 0.00521 -0.0769 0.5679 1.0000
4.250 0.8635 0.01239 0.00537 -0.0764 0.5561 1.0000
4.500 0.8889 0.01255 0.00551 -0.0758 0.5444 1.0000
4.750 0.9141 0.01272 0.00565 -0.0753 0.5318 1.0000
5.000 0.9388 0.01288 0.00580 -0.0746 0.5176 1.0000
5.250 0.9630 0.01305 0.00596 -0.0739 0.5016 1.0000
5.500 0.9867 0.01322 0.00615 -0.0731 0.4826 1.0000
5.750 1.0097 0.01342 0.00634 -0.0722 0.4606 1.0000
6.000 1.0319 0.01369 0.00654 -0.0712 0.4358 1.0000
6.250 1.0529 0.01405 0.00680 -0.0700 0.4074 1.0000
6.500 1.0728 0.01454 0.00715 -0.0686 0.3789 1.0000
6.750 1.0925 0.01511 0.00759 -0.0674 0.3535 1.0000
7.000 1.1118 0.01578 0.00810 -0.0661 0.3338 1.0000
7.250 1.1319 0.01643 0.00865 -0.0649 0.3177 1.0000
7.500 1.1527 0.01705 0.00923 -0.0639 0.3040 1.0000
7.750 1.1741 0.01763 0.00981 -0.0630 0.2925 1.0000
8.000 1.1955 0.01826 0.01041 -0.0622 0.2831 1.0000
8.250 1.2165 0.01887 0.01099 -0.0612 0.2740 1.0000
8.500 1.2373 0.01939 0.01158 -0.0603 0.2646 1.0000
8.750 1.2570 0.02001 0.01215 -0.0592 0.2555 1.0000
9.000 1.2755 0.02046 0.01267 -0.0580 0.2456 1.0000
9.250 1.2934 0.02099 0.01326 -0.0566 0.2361 1.0000
9.500 1.3105 0.02161 0.01383 -0.0552 0.2276 1.0000
9.750 1.3275 0.02205 0.01443 -0.0538 0.2193 1.0000
10.000 1.3421 0.02271 0.01506 -0.0520 0.2121 1.0000
10.250 1.3563 0.02316 0.01571 -0.0501 0.2042 1.0000
10.500 1.3682 0.02385 0.01642 -0.0480 0.1963 1.0000
10.750 1.3797 0.02446 0.01715 -0.0461 0.1859 1.0000
11.000 1.3906 0.02519 0.01799 -0.0442 0.1735 1.0000
11.250 1.3981 0.02618 0.01901 -0.0422 0.1558 1.0000
11.500 1.3972 0.02799 0.02059 -0.0398 0.1005 1.0000
11.750 1.3803 0.03137 0.02357 -0.0364 0.0649 1.0000
12.000 1.3713 0.03434 0.02654 -0.0340 0.0549 1.0000
12.250 1.3614 0.03755 0.02979 -0.0321 0.0499 1.0000
12.500 1.3600 0.04014 0.03252 -0.0308 0.0461 1.0000
12.750 1.3538 0.04328 0.03575 -0.0298 0.0434 1.0000
13.000 1.3414 0.04721 0.03974 -0.0290 0.0416 1.0000
13.250 1.3407 0.05006 0.04273 -0.0285 0.0399 1.0000
13.500 1.3375 0.05323 0.04602 -0.0281 0.0384 1.0000
13.750 1.3338 0.05654 0.04942 -0.0278 0.0371 1.0000
14.000 1.3293 0.05998 0.05292 -0.0277 0.0359 1.0000
14.250 1.3236 0.06350 0.05645 -0.0274 0.0348 1.0000
14.500 1.3216 0.06661 0.05962 -0.0269 0.0337 1.0000
14.750 1.3224 0.06961 0.06276 -0.0269 0.0327 1.0000
15.000 1.3230 0.07265 0.06591 -0.0269 0.0316 1.0000
15.250 1.3238 0.07564 0.06898 -0.0269 0.0307 1.0000
15.500 1.3255 0.07848 0.07187 -0.0268 0.0299 1.0000
15.750 1.3288 0.08099 0.07440 -0.0264 0.0291 1.0000
16.000 1.3377 0.08241 0.07578 -0.0246 0.0282 1.0000
16.250 1.3418 0.08498 0.07847 -0.0240 0.0277 1.0000
16.500 1.3408 0.08851 0.08219 -0.0245 0.0273 1.0000
16.750 1.3388 0.09220 0.08607 -0.0252 0.0268 1.0000
17.000 1.3360 0.09606 0.09009 -0.0260 0.0264 1.0000
17.250 1.3322 0.10014 0.09434 -0.0271 0.0259 1.0000
17.500 1.3280 0.10435 0.09871 -0.0284 0.0254 1.0000
17.750 1.3236 0.10866 0.10318 -0.0299 0.0250 1.0000
18.000 1.3188 0.11308 0.10774 -0.0316 0.0247 1.0000
18.250 1.3124 0.11788 0.11270 -0.0335 0.0245 1.0000
18.500 1.3040 0.12319 0.11819 -0.0360 0.0243 1.0000
18.750 1.2939 0.12902 0.12420 -0.0389 0.0242 1.0000
19.000 1.2815 0.13553 0.13091 -0.0426 0.0242 1.0000
19.250 1.2624 0.14383 0.13946 -0.0478 0.0243 1.0000
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