GOE 682 AIRFOIL (goe682-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 682 AIRFOIL (goe682-il) Reynolds number: 100,000 Max Cl/Cd: 57.45 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe682-il-100000-n5.txt Download as CSV file: xf-goe682-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 682 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3371 0.09155 0.08667 -0.0384 1.0000 0.0547
-8.250 -0.3492 0.08910 0.08431 -0.0371 1.0000 0.0537
-8.000 -0.3682 0.08686 0.08218 -0.0350 1.0000 0.0525
-7.750 -0.3746 0.08364 0.07902 -0.0365 0.9961 0.0525
-7.500 -0.3574 0.07842 0.07378 -0.0441 0.9870 0.0535
-7.250 -0.3398 0.07235 0.06766 -0.0529 0.9774 0.0539
-7.000 -0.3231 0.06511 0.06031 -0.0626 0.9673 0.0532
-6.750 -0.3058 0.05688 0.05187 -0.0723 0.9570 0.0526
-6.500 -0.2862 0.04938 0.04404 -0.0798 0.9480 0.0530
-6.250 -0.2618 0.04318 0.03740 -0.0855 0.9410 0.0547
-6.000 -0.2420 0.03805 0.03173 -0.0883 0.9318 0.0553
-5.750 -0.2123 0.03368 0.02673 -0.0916 0.9270 0.0560
-5.500 -0.1898 0.03092 0.02348 -0.0920 0.9179 0.0567
-5.250 -0.1573 0.02857 0.02055 -0.0938 0.9133 0.0585
-5.000 -0.1321 0.02699 0.01854 -0.0938 0.9047 0.0600
-4.750 -0.1003 0.02539 0.01678 -0.0950 0.8994 0.0615
-4.500 -0.0719 0.02420 0.01541 -0.0954 0.8922 0.0627
-4.250 -0.0416 0.02312 0.01415 -0.0959 0.8854 0.0643
-4.000 -0.0072 0.02205 0.01289 -0.0971 0.8805 0.0662
-3.750 0.0187 0.02131 0.01199 -0.0966 0.8710 0.0686
-3.500 0.0538 0.02056 0.01102 -0.0977 0.8654 0.0722
-3.250 0.0791 0.01973 0.01020 -0.0971 0.8548 0.0753
-3.000 0.1108 0.01901 0.00944 -0.0976 0.8471 0.0787
-2.750 0.1384 0.01845 0.00880 -0.0973 0.8371 0.0830
-2.500 0.1669 0.01791 0.00822 -0.0972 0.8285 0.0886
-2.250 0.1955 0.01746 0.00776 -0.0972 0.8200 0.0979
-2.000 0.2226 0.01704 0.00739 -0.0968 0.8110 0.1087
-1.750 0.2517 0.01663 0.00704 -0.0969 0.8031 0.1302
-1.500 0.2779 0.01630 0.00690 -0.0964 0.7937 0.1700
-1.250 0.3076 0.01600 0.00668 -0.0965 0.7861 0.2217
-1.000 0.3333 0.01581 0.00660 -0.0960 0.7761 0.2635
-0.750 0.3630 0.01554 0.00641 -0.0962 0.7685 0.3114
-0.500 0.3883 0.01526 0.00635 -0.0957 0.7585 0.3778
-0.250 0.4103 0.01436 0.00636 -0.0942 0.7502 0.6249
0.000 0.4755 0.01366 0.00618 -0.1008 0.7419 1.0000
0.250 0.5011 0.01376 0.00611 -0.1002 0.7324 1.0000
0.500 0.5280 0.01383 0.00602 -0.0997 0.7234 1.0000
0.750 0.5524 0.01397 0.00604 -0.0989 0.7129 1.0000
1.000 0.5789 0.01407 0.00600 -0.0983 0.7038 1.0000
1.250 0.6042 0.01419 0.00600 -0.0976 0.6930 1.0000
1.500 0.6287 0.01431 0.00602 -0.0968 0.6806 1.0000
1.750 0.6536 0.01442 0.00601 -0.0959 0.6672 1.0000
2.000 0.6782 0.01452 0.00600 -0.0949 0.6525 1.0000
2.250 0.7025 0.01464 0.00600 -0.0940 0.6374 1.0000
2.500 0.7271 0.01478 0.00604 -0.0931 0.6236 1.0000
2.750 0.7520 0.01494 0.00613 -0.0923 0.6114 1.0000
3.000 0.7759 0.01513 0.00628 -0.0914 0.5985 1.0000
3.250 0.8000 0.01532 0.00643 -0.0906 0.5857 1.0000
3.500 0.8241 0.01552 0.00659 -0.0897 0.5731 1.0000
3.750 0.8482 0.01572 0.00674 -0.0888 0.5599 1.0000
4.000 0.8719 0.01593 0.00691 -0.0879 0.5464 1.0000
4.250 0.8952 0.01616 0.00712 -0.0869 0.5322 1.0000
4.500 0.9182 0.01640 0.00734 -0.0859 0.5179 1.0000
4.750 0.9411 0.01666 0.00758 -0.0849 0.5033 1.0000
5.000 0.9637 0.01693 0.00783 -0.0839 0.4884 1.0000
5.250 0.9859 0.01723 0.00810 -0.0828 0.4731 1.0000
5.500 1.0078 0.01756 0.00839 -0.0816 0.4577 1.0000
5.750 1.0295 0.01792 0.00873 -0.0805 0.4426 1.0000
6.000 1.0509 0.01830 0.00910 -0.0793 0.4278 1.0000
6.250 1.0717 0.01871 0.00949 -0.0780 0.4126 1.0000
6.500 1.0921 0.01915 0.00992 -0.0767 0.3971 1.0000
6.750 1.1119 0.01961 0.01039 -0.0754 0.3815 1.0000
7.000 1.1315 0.02009 0.01088 -0.0740 0.3667 1.0000
7.250 1.1509 0.02059 0.01139 -0.0726 0.3528 1.0000
7.500 1.1699 0.02112 0.01192 -0.0712 0.3398 1.0000
7.750 1.1885 0.02168 0.01249 -0.0697 0.3276 1.0000
8.000 1.2068 0.02224 0.01309 -0.0683 0.3154 1.0000
8.250 1.2246 0.02284 0.01372 -0.0667 0.3041 1.0000
8.500 1.2414 0.02346 0.01435 -0.0651 0.2933 1.0000
8.750 1.2571 0.02411 0.01499 -0.0633 0.2830 1.0000
9.000 1.2730 0.02476 0.01574 -0.0616 0.2727 1.0000
9.250 1.2881 0.02546 0.01645 -0.0598 0.2648 1.0000
9.500 1.3027 0.02615 0.01724 -0.0579 0.2564 1.0000
9.750 1.3153 0.02690 0.01804 -0.0557 0.2476 1.0000
10.000 1.3250 0.02770 0.01887 -0.0533 0.2373 1.0000
10.250 1.3334 0.02854 0.01983 -0.0509 0.2258 1.0000
10.500 1.3395 0.02949 0.02083 -0.0483 0.2135 1.0000
10.750 1.3437 0.03056 0.02194 -0.0457 0.2002 1.0000
11.000 1.3477 0.03173 0.02317 -0.0433 0.1867 1.0000
11.250 1.3522 0.03300 0.02452 -0.0412 0.1731 1.0000
11.500 1.3571 0.03435 0.02597 -0.0393 0.1592 1.0000
11.750 1.3614 0.03587 0.02759 -0.0376 0.1424 1.0000
12.000 1.3610 0.03781 0.02955 -0.0359 0.1219 1.0000
12.250 1.3557 0.04034 0.03196 -0.0342 0.1001 1.0000
12.500 1.3472 0.04336 0.03488 -0.0328 0.0844 1.0000
12.750 1.3384 0.04666 0.03814 -0.0316 0.0711 1.0000
13.000 1.3299 0.05012 0.04164 -0.0309 0.0593 1.0000
13.250 1.3211 0.05380 0.04538 -0.0305 0.0515 1.0000
13.500 1.3118 0.05772 0.04939 -0.0304 0.0466 1.0000
13.750 1.3009 0.06206 0.05381 -0.0307 0.0430 1.0000
14.000 1.2882 0.06685 0.05870 -0.0315 0.0405 1.0000
14.250 1.2777 0.07161 0.06361 -0.0325 0.0384 1.0000
14.500 1.2660 0.07676 0.06891 -0.0338 0.0368 1.0000
14.750 1.2525 0.08242 0.07470 -0.0357 0.0355 1.0000
15.000 1.2387 0.08837 0.08078 -0.0378 0.0346 1.0000
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Polar data table (+)
Polar graphs
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