GOE 287 AIRFOIL (goe287-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 287 AIRFOIL (goe287-il) Reynolds number: 200,000 Max Cl/Cd: 80 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe287-il-200000.txt Download as CSV file: xf-goe287-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 287 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3790 0.11441 0.11123 -0.0053 1.0000 0.0308
-9.000 -0.3764 0.11214 0.10901 -0.0098 1.0000 0.0311
-8.750 -0.3721 0.10936 0.10628 -0.0141 1.0000 0.0312
-8.500 -0.3667 0.10622 0.10319 -0.0181 1.0000 0.0313
-8.250 -0.3596 0.10276 0.09978 -0.0227 1.0000 0.0314
-8.000 -0.3475 0.09584 0.09287 -0.0164 1.0000 0.0325
-7.750 -0.3369 0.09250 0.08955 -0.0169 1.0000 0.0335
-7.500 -0.3281 0.08932 0.08643 -0.0191 1.0000 0.0345
-7.250 -0.3185 0.08603 0.08319 -0.0226 1.0000 0.0355
-7.000 -0.2956 0.08161 0.07874 -0.0301 0.9660 0.0371
-6.750 -0.2767 0.07772 0.07480 -0.0368 0.9351 0.0390
-6.500 -0.2482 0.07441 0.07127 -0.0497 0.9035 0.0407
-6.250 -0.2292 0.07098 0.06764 -0.0539 0.8813 0.0409
-6.000 -0.2296 0.06517 0.06185 -0.0516 0.8639 0.0419
-5.750 -0.2221 0.06264 0.05927 -0.0490 0.8464 0.0431
-5.500 -0.2073 0.05998 0.05649 -0.0493 0.8301 0.0450
-5.250 -0.1862 0.05678 0.05312 -0.0519 0.8151 0.0475
-5.000 -0.1376 0.05422 0.04993 -0.0608 0.8011 0.0526
-4.750 -0.1233 0.04819 0.04385 -0.0622 0.7891 0.0540
-4.500 -0.1064 0.04559 0.04122 -0.0620 0.7770 0.0556
-4.250 -0.0845 0.04342 0.03892 -0.0626 0.7663 0.0592
-4.000 -0.0442 0.04051 0.03532 -0.0666 0.7560 0.0670
-3.750 -0.0244 0.03724 0.03213 -0.0670 0.7463 0.0689
-3.500 -0.0006 0.03527 0.03002 -0.0674 0.7382 0.0724
-3.250 0.0337 0.03309 0.02731 -0.0692 0.7290 0.0820
-3.000 0.0566 0.03095 0.02520 -0.0696 0.7222 0.0859
-2.750 0.0883 0.02930 0.02313 -0.0707 0.7145 0.0970
-2.500 0.1137 0.02748 0.02127 -0.0710 0.7088 0.1019
-2.250 0.1434 0.02592 0.01946 -0.0719 0.7021 0.1137
-2.000 0.1718 0.02461 0.01792 -0.0724 0.6960 0.1277
-1.750 0.1993 0.02336 0.01658 -0.0728 0.6896 0.1442
-1.000 0.2992 0.01823 0.01002 -0.0719 0.6704 0.0735
-0.750 0.3294 0.01736 0.00875 -0.0715 0.6653 0.0675
-0.500 0.3584 0.01663 0.00791 -0.0715 0.6595 0.0676
-0.250 0.3869 0.01593 0.00716 -0.0716 0.6537 0.0693
0.000 0.4152 0.01542 0.00654 -0.0714 0.6488 0.0689
0.250 0.4439 0.01492 0.00608 -0.0715 0.6423 0.0694
0.500 0.4721 0.01453 0.00567 -0.0714 0.6369 0.0710
0.750 0.5006 0.01427 0.00541 -0.0715 0.6319 0.0738
1.000 0.5293 0.01406 0.00522 -0.0716 0.6264 0.0780
1.250 0.5577 0.01387 0.00500 -0.0717 0.6213 0.0881
1.500 0.5865 0.01361 0.00486 -0.0718 0.6156 0.1246
1.750 0.6095 0.01160 0.00475 -0.0707 0.6098 1.0000
2.000 0.6376 0.01175 0.00473 -0.0706 0.6051 1.0000
2.250 0.6662 0.01189 0.00484 -0.0708 0.5993 1.0000
2.500 0.6943 0.01202 0.00490 -0.0708 0.5936 1.0000
2.750 0.7224 0.01217 0.00497 -0.0708 0.5881 1.0000
3.000 0.7505 0.01228 0.00509 -0.0709 0.5811 1.0000
3.250 0.7783 0.01243 0.00513 -0.0708 0.5752 1.0000
3.500 0.8064 0.01253 0.00529 -0.0710 0.5673 1.0000
3.750 0.8342 0.01266 0.00535 -0.0709 0.5608 1.0000
4.000 0.8620 0.01276 0.00552 -0.0710 0.5521 1.0000
4.250 0.8897 0.01287 0.00559 -0.0709 0.5442 1.0000
4.500 0.9173 0.01294 0.00571 -0.0708 0.5339 1.0000
4.750 0.9447 0.01301 0.00583 -0.0708 0.5225 1.0000
5.000 0.9719 0.01305 0.00591 -0.0706 0.5091 1.0000
5.250 0.9989 0.01308 0.00597 -0.0705 0.4922 1.0000
5.500 1.0257 0.01311 0.00601 -0.0703 0.4708 1.0000
5.750 1.0520 0.01315 0.00604 -0.0701 0.4330 1.0000
6.000 1.0762 0.01349 0.00611 -0.0697 0.3796 1.0000
6.500 1.1223 0.01485 0.00708 -0.0690 0.3211 1.0000
6.750 1.1459 0.01548 0.00764 -0.0686 0.3035 1.0000
7.000 1.1687 0.01614 0.00823 -0.0683 0.2801 1.0000
7.250 1.1910 0.01680 0.00881 -0.0679 0.2529 1.0000
7.500 1.2122 0.01759 0.00944 -0.0673 0.2128 1.0000
7.750 1.2221 0.01971 0.01074 -0.0658 0.0930 1.0000
8.000 1.2314 0.02185 0.01252 -0.0639 0.0406 1.0000
8.250 1.2494 0.02286 0.01372 -0.0628 0.0373 1.0000
8.500 1.2648 0.02405 0.01509 -0.0614 0.0350 1.0000
8.750 1.2752 0.02557 0.01679 -0.0596 0.0329 1.0000
9.000 1.2768 0.02756 0.01897 -0.0570 0.0313 1.0000
9.250 1.2819 0.02899 0.02050 -0.0546 0.0304 1.0000
9.500 1.2844 0.03083 0.02247 -0.0526 0.0299 1.0000
9.750 1.2865 0.03293 0.02467 -0.0510 0.0294 1.0000
10.000 1.2887 0.03519 0.02702 -0.0496 0.0289 1.0000
10.250 1.2918 0.03747 0.02938 -0.0483 0.0285 1.0000
10.500 1.2961 0.03967 0.03166 -0.0470 0.0282 1.0000
10.750 1.3025 0.04173 0.03380 -0.0455 0.0278 1.0000
11.000 1.3109 0.04364 0.03575 -0.0440 0.0272 1.0000
11.250 1.3211 0.04545 0.03758 -0.0425 0.0262 1.0000
11.500 1.3340 0.04718 0.03933 -0.0409 0.0254 1.0000
11.750 1.3525 0.04875 0.04097 -0.0391 0.0253 1.0000
12.000 1.3739 0.05044 0.04279 -0.0374 0.0256 1.0000
12.250 1.3910 0.05268 0.04532 -0.0358 0.0265 1.0000
12.500 1.4108 0.05559 0.04853 -0.0341 0.0283 1.0000
12.750 1.2466 0.05317 0.04651 -0.0227 0.0266 1.0000
13.000 1.2573 0.05641 0.05002 -0.0210 0.0276 1.0000
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Polar data table (+)
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