GOE 287 AIRFOIL (goe287-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 287 AIRFOIL (goe287-il) Reynolds number: 100,000 Max Cl/Cd: 59.54 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe287-il-100000-n5.txt Download as CSV file: xf-goe287-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3727 0.12271 0.11817 -0.0074 1.0000 0.0364
-9.500 -0.3706 0.12073 0.11624 -0.0112 1.0000 0.0369
-9.250 -0.3673 0.11830 0.11387 -0.0148 1.0000 0.0371
-9.000 -0.3626 0.11545 0.11108 -0.0181 1.0000 0.0373
-8.750 -0.3573 0.11230 0.10799 -0.0212 1.0000 0.0374
-8.500 -0.3489 0.10619 0.10193 -0.0210 1.0000 0.0379
-8.250 -0.3348 0.10104 0.09678 -0.0188 1.0000 0.0390
-8.000 -0.3257 0.09755 0.09331 -0.0196 1.0000 0.0401
-7.750 -0.3181 0.09435 0.09017 -0.0212 1.0000 0.0412
-7.500 -0.3104 0.09124 0.08711 -0.0236 0.9842 0.0426
-7.250 -0.2945 0.08754 0.08340 -0.0289 0.9497 0.0458
-7.000 -0.2737 0.08437 0.08015 -0.0426 0.9137 0.0497
-6.750 -0.2523 0.08073 0.07634 -0.0514 0.8881 0.0502
-6.500 -0.2424 0.07567 0.07125 -0.0522 0.8701 0.0507
-6.250 -0.2363 0.07197 0.06754 -0.0488 0.8544 0.0520
-6.000 -0.2243 0.06888 0.06437 -0.0486 0.8393 0.0536
-5.750 -0.2081 0.06575 0.06112 -0.0503 0.8250 0.0564
-5.250 -0.1585 0.05784 0.05275 -0.0608 0.7996 0.0654
-5.000 -0.1414 0.05487 0.04970 -0.0609 0.7881 0.0676
-4.750 -0.1186 0.05182 0.04647 -0.0628 0.7776 0.0707
-4.500 -0.0817 0.04824 0.04237 -0.0687 0.7668 0.0790
-4.250 -0.0654 0.04549 0.03968 -0.0680 0.7569 0.0826
-4.000 -0.0291 0.04047 0.03409 -0.0711 0.7490 0.0606
-3.750 -0.0002 0.03676 0.03003 -0.0727 0.7398 0.0550
-3.500 0.0279 0.03439 0.02730 -0.0736 0.7319 0.0565
-3.250 0.0578 0.03180 0.02432 -0.0746 0.7233 0.0557
-3.000 0.0894 0.02899 0.02090 -0.0753 0.7162 0.0528
-2.750 0.1202 0.02694 0.01829 -0.0757 0.7085 0.0516
-2.500 0.1490 0.02543 0.01638 -0.0759 0.7022 0.0515
-2.250 0.1769 0.02434 0.01517 -0.0763 0.6951 0.0536
-2.000 0.2051 0.02340 0.01397 -0.0764 0.6898 0.0556
-1.750 0.2346 0.02231 0.01258 -0.0766 0.6837 0.0554
-1.500 0.2636 0.02136 0.01137 -0.0766 0.6784 0.0552
-1.250 0.2921 0.02056 0.01033 -0.0765 0.6738 0.0552
-1.000 0.3209 0.01988 0.00952 -0.0766 0.6679 0.0556
-0.750 0.3491 0.01930 0.00881 -0.0765 0.6630 0.0563
-0.500 0.3770 0.01879 0.00821 -0.0764 0.6583 0.0573
-0.250 0.4049 0.01836 0.00775 -0.0764 0.6519 0.0588
0.000 0.4322 0.01802 0.00730 -0.0761 0.6459 0.0616
0.250 0.4597 0.01771 0.00699 -0.0761 0.6383 0.0660
0.500 0.4867 0.01746 0.00665 -0.0757 0.6312 0.0698
0.750 0.5144 0.01730 0.00642 -0.0756 0.6231 0.0735
1.000 0.5423 0.01716 0.00616 -0.0754 0.6167 0.0794
1.250 0.5707 0.01703 0.00604 -0.0755 0.6100 0.0964
1.500 0.5954 0.01487 0.00595 -0.0748 0.6038 1.0000
1.750 0.6231 0.01503 0.00591 -0.0747 0.5972 1.0000
2.000 0.6507 0.01518 0.00592 -0.0746 0.5897 1.0000
2.250 0.6782 0.01534 0.00596 -0.0745 0.5828 1.0000
2.500 0.7057 0.01551 0.00607 -0.0745 0.5756 1.0000
2.750 0.7332 0.01568 0.00613 -0.0743 0.5702 1.0000
3.000 0.7608 0.01589 0.00637 -0.0744 0.5631 1.0000
3.250 0.7881 0.01606 0.00647 -0.0743 0.5569 1.0000
3.500 0.8153 0.01626 0.00670 -0.0743 0.5490 1.0000
3.750 0.8425 0.01642 0.00684 -0.0741 0.5417 1.0000
4.000 0.8695 0.01662 0.00710 -0.0741 0.5325 1.0000
4.250 0.8963 0.01679 0.00726 -0.0739 0.5240 1.0000
4.500 0.9231 0.01698 0.00753 -0.0739 0.5139 1.0000
4.750 0.9497 0.01718 0.00781 -0.0737 0.5033 1.0000
5.000 0.9761 0.01737 0.00806 -0.0736 0.4919 1.0000
5.250 1.0024 0.01756 0.00835 -0.0734 0.4787 1.0000
5.500 1.0284 0.01778 0.00867 -0.0732 0.4629 1.0000
5.750 1.0541 0.01800 0.00900 -0.0729 0.4441 1.0000
6.000 1.0793 0.01824 0.00929 -0.0726 0.4222 1.0000
6.250 1.1038 0.01854 0.00962 -0.0722 0.3967 1.0000
6.500 1.1274 0.01895 0.00996 -0.0716 0.3740 1.0000
6.750 1.1487 0.01956 0.01039 -0.0708 0.3471 1.0000
7.000 1.1667 0.02052 0.01107 -0.0698 0.3132 1.0000
7.250 1.1856 0.02143 0.01190 -0.0690 0.2878 1.0000
7.500 1.2048 0.02228 0.01273 -0.0682 0.2672 1.0000
7.750 1.2223 0.02323 0.01363 -0.0673 0.2387 1.0000
8.000 1.2394 0.02420 0.01456 -0.0663 0.2077 1.0000
8.250 1.2434 0.02635 0.01599 -0.0643 0.1067 1.0000
8.500 1.2408 0.02922 0.01830 -0.0615 0.0399 1.0000
8.750 1.2483 0.03098 0.02017 -0.0595 0.0338 1.0000
9.000 1.2556 0.03252 0.02189 -0.0574 0.0314 1.0000
9.250 1.2614 0.03413 0.02371 -0.0554 0.0297 1.0000
9.500 1.2651 0.03605 0.02582 -0.0537 0.0280 1.0000
9.750 1.2659 0.03835 0.02831 -0.0523 0.0263 1.0000
10.000 1.2635 0.04112 0.03127 -0.0512 0.0251 1.0000
10.250 1.2577 0.04441 0.03475 -0.0505 0.0242 1.0000
10.500 1.2502 0.04804 0.03858 -0.0501 0.0236 1.0000
10.750 1.2457 0.05146 0.04215 -0.0498 0.0233 1.0000
11.000 1.2427 0.05481 0.04566 -0.0497 0.0230 1.0000
11.250 1.2396 0.05820 0.04922 -0.0496 0.0226 1.0000
11.500 1.2371 0.06153 0.05272 -0.0495 0.0222 1.0000
11.750 1.2358 0.06468 0.05600 -0.0492 0.0217 1.0000
12.000 1.2361 0.06762 0.05905 -0.0488 0.0210 1.0000
12.250 1.2377 0.07037 0.06190 -0.0483 0.0201 1.0000
12.500 1.2410 0.07286 0.06447 -0.0476 0.0193 1.0000
12.750 1.2473 0.07493 0.06661 -0.0465 0.0186 1.0000
13.000 1.2571 0.07661 0.06834 -0.0449 0.0181 1.0000
13.250 1.2678 0.07835 0.07016 -0.0434 0.0177 1.0000
13.500 1.2784 0.08028 0.07218 -0.0419 0.0173 1.0000
13.750 1.2881 0.08251 0.07457 -0.0407 0.0170 1.0000
14.000 1.2959 0.08514 0.07730 -0.0397 0.0165 1.0000
14.250 1.3056 0.08803 0.08028 -0.0384 0.0159 1.0000
14.500 1.3080 0.09223 0.08465 -0.0377 0.0154 1.0000
14.750 1.2976 0.09670 0.08936 -0.0392 0.0153 1.0000
15.000 1.2875 0.10143 0.09434 -0.0408 0.0151 1.0000
15.250 1.2776 0.10644 0.09959 -0.0428 0.0150 1.0000
15.500 1.2670 0.11178 0.10516 -0.0451 0.0149 1.0000
15.750 1.2562 0.11743 0.11104 -0.0478 0.0149 1.0000
16.000 1.2451 0.12341 0.11723 -0.0509 0.0149 1.0000
16.250 1.2336 0.12975 0.12378 -0.0545 0.0149 1.0000
16.500 1.2221 0.13644 0.13067 -0.0585 0.0149 1.0000
16.750 1.2103 0.14353 0.13794 -0.0629 0.0149 1.0000
17.000 1.1984 0.15100 0.14560 -0.0678 0.0150 1.0000
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