GOE 269 AIRFOIL (goe269-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 269 AIRFOIL (goe269-il) Reynolds number: 100,000 Max Cl/Cd: 61.5 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe269-il-100000-n5.txt Download as CSV file: xf-goe269-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 269 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 -0.3479 0.10774 0.10276 -0.0155 1.0000 0.0486
-8.250 -0.3483 0.10631 0.10140 -0.0188 1.0000 0.0491
-8.000 -0.3463 0.10442 0.09958 -0.0229 1.0000 0.0493
-7.750 -0.3379 0.10161 0.09680 -0.0278 1.0000 0.0494
-7.500 -0.3283 0.09578 0.09099 -0.0224 1.0000 0.0501
-7.250 -0.3192 0.09230 0.08754 -0.0218 1.0000 0.0511
-7.000 -0.3108 0.08938 0.08466 -0.0226 1.0000 0.0523
-6.750 -0.3027 0.08673 0.08206 -0.0239 1.0000 0.0545
-6.500 -0.2941 0.08442 0.07980 -0.0273 1.0000 0.0577
-6.250 -0.2813 0.08250 0.07790 -0.0348 1.0000 0.0589
-6.000 -0.2690 0.07996 0.07533 -0.0393 1.0000 0.0591
-5.750 -0.2470 0.07647 0.07179 -0.0449 0.9973 0.0593
-5.500 -0.2346 0.07144 0.06683 -0.0429 0.9915 0.0602
-5.250 -0.2120 0.06787 0.06325 -0.0441 0.9850 0.0628
-5.000 -0.1734 0.06407 0.05934 -0.0518 0.9762 0.0675
-4.750 -0.1085 0.05984 0.05470 -0.0679 0.9672 0.0699
-4.500 -0.0685 0.05536 0.05003 -0.0745 0.9598 0.0703
-4.250 -0.0524 0.05170 0.04652 -0.0737 0.9511 0.0723
-4.000 -0.0199 0.04886 0.04360 -0.0771 0.9418 0.0761
-3.750 0.0230 0.04552 0.04005 -0.0832 0.9338 0.0785
-3.250 0.1174 0.03634 0.02990 -0.0952 0.9126 0.0590
-3.000 0.1431 0.03489 0.02853 -0.0960 0.8981 0.0627
-2.500 0.2187 0.02896 0.02158 -0.1007 0.8704 0.0590
-2.250 0.2497 0.02698 0.01928 -0.1015 0.8574 0.0590
-2.000 0.2804 0.02517 0.01711 -0.1021 0.8439 0.0592
-1.750 0.3091 0.02374 0.01548 -0.1024 0.8304 0.0600
-1.500 0.3363 0.02306 0.01476 -0.1025 0.8168 0.0623
-1.250 0.3652 0.02218 0.01366 -0.1026 0.8037 0.0654
-1.000 0.3950 0.02104 0.01219 -0.1026 0.7912 0.0669
-0.750 0.4244 0.02002 0.01083 -0.1024 0.7791 0.0683
-0.500 0.4534 0.01917 0.00964 -0.1021 0.7672 0.0702
-0.250 0.4810 0.01849 0.00890 -0.1019 0.7543 0.0727
0.000 0.5085 0.01811 0.00844 -0.1016 0.7418 0.0779
0.250 0.5363 0.01764 0.00780 -0.1012 0.7297 0.0836
0.500 0.5635 0.01720 0.00732 -0.1008 0.7178 0.0878
0.750 0.5907 0.01696 0.00696 -0.1003 0.7056 0.0950
1.000 0.6176 0.01663 0.00668 -0.1000 0.6928 0.1018
1.250 0.6444 0.01641 0.00642 -0.0995 0.6800 0.1075
1.500 0.6712 0.01626 0.00625 -0.0990 0.6673 0.1157
1.750 0.6984 0.01618 0.00611 -0.0986 0.6546 0.1225
2.000 0.7255 0.01614 0.00599 -0.0981 0.6416 0.1283
2.250 0.7526 0.01614 0.00599 -0.0978 0.6278 0.1393
2.500 0.7798 0.01615 0.00602 -0.0974 0.6134 0.1523
2.750 0.8069 0.01616 0.00606 -0.0971 0.5990 0.1728
3.000 0.8292 0.01471 0.00612 -0.0959 0.5849 1.0000
3.250 0.8560 0.01494 0.00621 -0.0954 0.5699 1.0000
3.500 0.8827 0.01517 0.00635 -0.0950 0.5547 1.0000
3.750 0.9091 0.01541 0.00651 -0.0946 0.5393 1.0000
4.000 0.9352 0.01564 0.00667 -0.0940 0.5213 1.0000
4.250 0.9606 0.01589 0.00681 -0.0934 0.4996 1.0000
4.500 0.9857 0.01618 0.00696 -0.0928 0.4767 1.0000
4.750 1.0107 0.01652 0.00720 -0.0921 0.4576 1.0000
5.250 1.0616 0.01727 0.00787 -0.0912 0.4290 1.0000
5.500 1.0867 0.01767 0.00826 -0.0907 0.4149 1.0000
5.750 1.1117 0.01808 0.00870 -0.0901 0.4005 1.0000
6.000 1.1364 0.01851 0.00916 -0.0896 0.3863 1.0000
6.250 1.1611 0.01894 0.00964 -0.0891 0.3724 1.0000
6.500 1.1853 0.01939 0.01016 -0.0885 0.3572 1.0000
6.750 1.2090 0.01985 0.01067 -0.0878 0.3402 1.0000
7.000 1.2322 0.02035 0.01121 -0.0871 0.3216 1.0000
7.250 1.2549 0.02087 0.01178 -0.0863 0.3009 1.0000
7.500 1.2766 0.02147 0.01242 -0.0854 0.2768 1.0000
7.750 1.2974 0.02215 0.01310 -0.0845 0.2507 1.0000
8.000 1.3172 0.02296 0.01386 -0.0834 0.2269 1.0000
8.250 1.3362 0.02384 0.01472 -0.0823 0.2064 1.0000
8.500 1.3541 0.02482 0.01566 -0.0810 0.1891 1.0000
8.750 1.3708 0.02588 0.01671 -0.0797 0.1732 1.0000
9.000 1.3869 0.02696 0.01778 -0.0784 0.1575 1.0000
9.250 1.4022 0.02806 0.01890 -0.0770 0.1428 1.0000
9.500 1.4165 0.02919 0.02006 -0.0755 0.1289 1.0000
9.750 1.4300 0.03034 0.02125 -0.0739 0.1151 1.0000
10.000 1.4429 0.03149 0.02253 -0.0723 0.1014 1.0000
10.250 1.4556 0.03263 0.02380 -0.0706 0.0861 1.0000
10.500 1.4639 0.03404 0.02525 -0.0685 0.0684 1.0000
10.750 1.4636 0.03591 0.02704 -0.0655 0.0544 1.0000
11.000 1.4616 0.03809 0.02923 -0.0628 0.0446 1.0000
11.250 1.4594 0.04048 0.03169 -0.0605 0.0386 1.0000
11.500 1.4554 0.04319 0.03448 -0.0587 0.0350 1.0000
11.750 1.4519 0.04604 0.03747 -0.0572 0.0327 1.0000
12.000 1.4482 0.04909 0.04069 -0.0562 0.0308 1.0000
12.250 1.4432 0.05248 0.04422 -0.0556 0.0292 1.0000
12.500 1.4359 0.05630 0.04818 -0.0555 0.0281 1.0000
12.750 1.4275 0.06045 0.05248 -0.0557 0.0271 1.0000
13.000 1.4211 0.06449 0.05673 -0.0560 0.0261 1.0000
13.250 1.4136 0.06881 0.06124 -0.0565 0.0253 1.0000
13.500 1.4051 0.07338 0.06598 -0.0574 0.0245 1.0000
13.750 1.3957 0.07820 0.07096 -0.0585 0.0239 1.0000
14.000 1.3859 0.08322 0.07614 -0.0598 0.0234 1.0000
14.250 1.3760 0.08840 0.08147 -0.0613 0.0230 1.0000
14.500 1.3664 0.09368 0.08689 -0.0629 0.0226 1.0000
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Polar data table (+)
Polar graphs
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