GOE 506 AIRFOIL (goe506-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 506 AIRFOIL (goe506-il) Reynolds number: 100,000 Max Cl/Cd: 40.65 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe506-il-100000-n5.txt Download as CSV file: xf-goe506-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 506 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2844 0.09544 0.09054 -0.0865 0.9639 0.0334
-11.250 -0.3092 0.08483 0.07991 -0.0935 0.9601 0.0330
-11.000 -0.3470 0.07355 0.06852 -0.1020 0.9532 0.0322
-10.750 -0.3799 0.06313 0.05783 -0.1135 0.9475 0.0314
-10.500 -0.4093 0.05842 0.05290 -0.1158 0.9376 0.0309
-10.250 -0.4299 0.05522 0.04948 -0.1156 0.9308 0.0312
-10.000 -0.4503 0.05314 0.04720 -0.1121 0.9221 0.0314
-9.500 -0.4698 0.04846 0.04193 -0.1065 0.9083 0.0323
-9.250 -0.4675 0.04588 0.03892 -0.1051 0.9038 0.0332
-9.000 -0.4696 0.04410 0.03680 -0.1017 0.8981 0.0337
-8.750 -0.4702 0.04255 0.03492 -0.0980 0.8921 0.0341
-8.500 -0.4581 0.04055 0.03256 -0.0966 0.8889 0.0347
-8.250 -0.4375 0.03866 0.03059 -0.0965 0.8869 0.0358
-8.000 -0.4361 0.03791 0.02977 -0.0925 0.8807 0.0368
-7.750 -0.4233 0.03687 0.02859 -0.0905 0.8763 0.0382
-7.500 -0.4037 0.03565 0.02716 -0.0896 0.8737 0.0398
-7.250 -0.3805 0.03442 0.02570 -0.0892 0.8718 0.0411
-7.000 -0.3553 0.03327 0.02436 -0.0890 0.8703 0.0427
-6.750 -0.3618 0.03297 0.02410 -0.0834 0.8631 0.0436
-6.500 -0.3438 0.03217 0.02330 -0.0821 0.8599 0.0455
-6.250 -0.3210 0.03138 0.02244 -0.0814 0.8575 0.0474
-6.000 -0.2965 0.03064 0.02159 -0.0810 0.8558 0.0492
-5.750 -0.2888 0.03046 0.02129 -0.0777 0.8513 0.0510
-5.500 -0.2796 0.02997 0.02081 -0.0747 0.8462 0.0529
-5.250 -0.2541 0.02924 0.02002 -0.0744 0.8427 0.0557
-5.000 -0.2186 0.02834 0.01895 -0.0757 0.8399 0.0590
-4.750 -0.2131 0.02819 0.01871 -0.0717 0.8312 0.0616
-4.500 -0.1800 0.02720 0.01764 -0.0725 0.8268 0.0674
-4.250 -0.1555 0.02660 0.01693 -0.0716 0.8211 0.0736
-4.000 -0.1346 0.02585 0.01620 -0.0702 0.8137 0.0859
-3.750 -0.1010 0.02455 0.01554 -0.0713 0.8103 0.2083
-3.500 -0.0867 0.02452 0.01544 -0.0687 0.8008 0.2333
-3.250 -0.0508 0.02394 0.01484 -0.0696 0.7962 0.2602
-3.000 -0.0310 0.02382 0.01467 -0.0680 0.7887 0.2790
-2.750 -0.0034 0.02347 0.01428 -0.0676 0.7828 0.2945
-2.500 0.0318 0.02294 0.01371 -0.0685 0.7798 0.3117
-2.250 0.0434 0.02310 0.01385 -0.0656 0.7710 0.3214
-2.000 0.0733 0.02269 0.01344 -0.0657 0.7667 0.3387
-1.750 0.1096 0.02206 0.01281 -0.0667 0.7638 0.3576
-1.500 0.1194 0.02224 0.01301 -0.0635 0.7536 0.3697
-1.250 0.1548 0.02160 0.01237 -0.0644 0.7495 0.3861
-1.000 0.1708 0.02158 0.01236 -0.0622 0.7399 0.4012
-0.750 0.2041 0.02096 0.01181 -0.0627 0.7342 0.4250
-0.500 0.2225 0.02083 0.01176 -0.0609 0.7240 0.4528
-0.250 0.2572 0.02016 0.01124 -0.0617 0.7176 0.5002
0.250 0.2983 0.01949 0.01118 -0.0584 0.6953 0.6579
0.500 0.4022 0.01864 0.01091 -0.0724 0.6844 0.8917
0.750 0.4747 0.01873 0.01094 -0.0815 0.6633 0.9824
1.000 0.5028 0.01882 0.01088 -0.0817 0.6387 1.0000
1.250 0.5226 0.01865 0.01051 -0.0798 0.6060 1.0000
1.500 0.5628 0.01812 0.00955 -0.0813 0.5649 1.0000
1.750 0.5905 0.01809 0.00906 -0.0809 0.5301 1.0000
2.000 0.6079 0.01836 0.00901 -0.0790 0.5054 1.0000
2.250 0.6244 0.01868 0.00909 -0.0769 0.4860 1.0000
2.500 0.6404 0.01902 0.00924 -0.0749 0.4694 1.0000
2.750 0.6575 0.01934 0.00940 -0.0731 0.4560 1.0000
3.000 0.6755 0.01966 0.00956 -0.0715 0.4444 1.0000
3.250 0.6938 0.01997 0.00976 -0.0699 0.4343 1.0000
3.500 0.7129 0.02028 0.00996 -0.0685 0.4255 1.0000
3.750 0.7327 0.02058 0.01017 -0.0673 0.4177 1.0000
4.000 0.7536 0.02088 0.01037 -0.0662 0.4112 1.0000
4.250 0.7745 0.02118 0.01061 -0.0652 0.4051 1.0000
4.500 0.7957 0.02150 0.01085 -0.0642 0.3995 1.0000
4.750 0.8165 0.02182 0.01111 -0.0632 0.3938 1.0000
5.000 0.8370 0.02215 0.01140 -0.0622 0.3882 1.0000
5.250 0.8583 0.02250 0.01168 -0.0613 0.3834 1.0000
5.500 0.8805 0.02284 0.01198 -0.0606 0.3794 1.0000
5.750 0.9019 0.02318 0.01234 -0.0598 0.3753 1.0000
6.000 0.9235 0.02354 0.01270 -0.0590 0.3714 1.0000
6.250 0.9463 0.02391 0.01303 -0.0584 0.3682 1.0000
6.500 0.9697 0.02429 0.01336 -0.0580 0.3649 1.0000
6.750 0.9898 0.02469 0.01383 -0.0570 0.3612 1.0000
7.000 1.0107 0.02510 0.01428 -0.0562 0.3577 1.0000
7.250 1.0308 0.02552 0.01472 -0.0552 0.3538 1.0000
7.500 1.0524 0.02594 0.01510 -0.0546 0.3500 1.0000
7.750 1.0704 0.02641 0.01564 -0.0533 0.3458 1.0000
8.000 1.0883 0.02689 0.01620 -0.0522 0.3420 1.0000
8.250 1.1076 0.02737 0.01674 -0.0512 0.3385 1.0000
8.500 1.1281 0.02784 0.01726 -0.0504 0.3354 1.0000
8.750 1.1505 0.02830 0.01769 -0.0499 0.3319 1.0000
9.000 1.1631 0.02891 0.01846 -0.0481 0.3277 1.0000
9.250 1.1782 0.02950 0.01916 -0.0466 0.3236 1.0000
9.500 1.1954 0.03006 0.01979 -0.0454 0.3200 1.0000
9.750 1.2145 0.03060 0.02037 -0.0446 0.3166 1.0000
10.000 1.2307 0.03123 0.02110 -0.0433 0.3130 1.0000
10.250 1.2416 0.03199 0.02203 -0.0415 0.3088 1.0000
10.500 1.2548 0.03270 0.02286 -0.0399 0.3047 1.0000
10.750 1.2700 0.03334 0.02358 -0.0386 0.3007 1.0000
11.000 1.2834 0.03407 0.02439 -0.0372 0.2965 1.0000
11.250 1.2875 0.03510 0.02563 -0.0347 0.2909 1.0000
11.500 1.2933 0.03597 0.02656 -0.0325 0.2844 1.0000
11.750 1.2950 0.03711 0.02784 -0.0300 0.2776 1.0000
12.000 1.2954 0.03831 0.02916 -0.0275 0.2697 1.0000
12.250 1.2956 0.03970 0.03070 -0.0252 0.2617 1.0000
12.500 1.2969 0.04107 0.03218 -0.0232 0.2542 1.0000
12.750 1.2962 0.04278 0.03406 -0.0212 0.2451 1.0000
13.000 1.2962 0.04450 0.03588 -0.0195 0.2369 1.0000
13.250 1.2945 0.04647 0.03797 -0.0178 0.2276 1.0000
13.500 1.2910 0.04874 0.04034 -0.0163 0.2169 1.0000
13.750 1.2884 0.05109 0.04277 -0.0151 0.2084 1.0000
14.000 1.2818 0.05388 0.04558 -0.0139 0.1993 1.0000
14.250 1.2725 0.05712 0.04884 -0.0129 0.1908 1.0000
14.500 1.2617 0.06073 0.05248 -0.0121 0.1839 1.0000
14.750 1.2480 0.06488 0.05663 -0.0117 0.1776 1.0000
15.000 1.2369 0.06900 0.06084 -0.0117 0.1730 1.0000
15.250 1.2241 0.07356 0.06550 -0.0120 0.1683 1.0000
15.500 1.2119 0.07814 0.07015 -0.0124 0.1642 1.0000
15.750 1.1991 0.08295 0.07503 -0.0131 0.1593 1.0000
16.000 1.1856 0.08812 0.08037 -0.0142 0.1545 1.0000
16.250 1.1721 0.09320 0.08549 -0.0153 0.1486 1.0000
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