GOE 408 AIRFOIL (goe408-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 408 AIRFOIL (goe408-il) Reynolds number: 1,000,000 Max Cl/Cd: 102.17 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe408-il-1000000-n5.txt Download as CSV file: xf-goe408-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 408 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4045 0.08628 0.08469 -0.0320 0.9950 0.0054
-8.500 -0.4533 0.06039 0.05867 -0.0587 0.9871 0.0060
-8.250 -0.4541 0.05291 0.05104 -0.0631 0.9824 0.0061
-8.000 -0.4403 0.04589 0.04381 -0.0682 0.9797 0.0062
-7.750 -0.4366 0.03804 0.03563 -0.0700 0.9755 0.0063
-7.500 -0.4287 0.03211 0.02937 -0.0697 0.9709 0.0064
-7.000 -0.4242 0.02021 0.01651 -0.0635 0.9592 0.0073
-6.750 -0.4296 0.01494 0.01068 -0.0576 0.9498 0.0077
-6.500 -0.4141 0.01359 0.00914 -0.0552 0.9408 0.0080
-6.000 -0.3658 0.01194 0.00719 -0.0536 0.9224 0.0091
-5.750 -0.3270 0.01098 0.00609 -0.0560 0.9133 0.0103
-5.500 -0.2693 0.00992 0.00487 -0.0627 0.9021 0.0123
-5.250 -0.1996 0.00913 0.00398 -0.0724 0.8838 0.0195
-5.000 -0.1385 0.00909 0.00385 -0.0800 0.8581 0.0255
-4.750 -0.0983 0.00937 0.00403 -0.0828 0.8233 0.0278
-4.500 -0.0720 0.00948 0.00396 -0.0823 0.7886 0.0293
-4.250 -0.0487 0.00958 0.00391 -0.0812 0.7617 0.0304
-4.000 -0.0252 0.00959 0.00379 -0.0801 0.7422 0.0308
-3.750 -0.0020 0.00945 0.00356 -0.0790 0.7261 0.0318
-3.500 0.0230 0.00963 0.00370 -0.0783 0.7119 0.0329
-3.250 0.0482 0.00987 0.00392 -0.0776 0.6993 0.0339
-3.000 0.0725 0.00970 0.00367 -0.0767 0.6899 0.0345
-2.750 0.0967 0.00955 0.00343 -0.0758 0.6783 0.0351
-2.500 0.1211 0.00937 0.00319 -0.0750 0.6688 0.0358
-2.250 0.1453 0.00921 0.00296 -0.0741 0.6593 0.0363
-2.000 0.1696 0.00906 0.00275 -0.0732 0.6492 0.0367
-1.750 0.1937 0.00890 0.00253 -0.0723 0.6393 0.0371
-1.500 0.2174 0.00876 0.00233 -0.0713 0.6289 0.0373
-1.250 0.2416 0.00867 0.00219 -0.0704 0.6188 0.0376
-1.000 0.2658 0.00858 0.00205 -0.0695 0.6087 0.0379
-0.750 0.2896 0.00848 0.00190 -0.0685 0.5987 0.0381
-0.250 0.3369 0.00831 0.00163 -0.0666 0.5743 0.0388
0.000 0.3602 0.00819 0.00147 -0.0655 0.5617 0.0400
0.250 0.3836 0.00822 0.00142 -0.0645 0.5404 0.0411
0.500 0.4077 0.00824 0.00138 -0.0636 0.5229 0.0418
0.750 0.4318 0.00830 0.00136 -0.0627 0.5015 0.0428
1.000 0.4558 0.00834 0.00134 -0.0619 0.4837 0.0435
1.250 0.4802 0.00839 0.00134 -0.0611 0.4676 0.0447
1.500 0.5043 0.00848 0.00135 -0.0603 0.4480 0.0457
1.750 0.5284 0.00857 0.00137 -0.0594 0.4294 0.0462
2.000 0.5526 0.00865 0.00139 -0.0586 0.4143 0.0469
2.250 0.5767 0.00874 0.00144 -0.0578 0.3998 0.0474
2.500 0.6008 0.00879 0.00146 -0.0570 0.3886 0.0484
2.750 0.6249 0.00883 0.00148 -0.0562 0.3793 0.0515
3.000 0.6490 0.00889 0.00154 -0.0553 0.3701 0.0532
3.250 0.6728 0.00897 0.00160 -0.0545 0.3594 0.0564
3.500 0.6966 0.00904 0.00166 -0.0536 0.3497 0.0589
3.750 0.7202 0.00913 0.00174 -0.0527 0.3390 0.0647
4.000 0.7423 0.00930 0.00190 -0.0516 0.3116 0.1119
4.500 1.0125 0.00991 0.00366 -0.1039 0.1666 1.0000
4.750 1.0346 0.01015 0.00385 -0.1027 0.1541 1.0000
5.000 1.0567 0.01040 0.00405 -0.1016 0.1434 1.0000
5.250 1.0784 0.01066 0.00426 -0.1003 0.1312 1.0000
5.500 1.0997 0.01095 0.00450 -0.0990 0.1177 1.0000
5.750 1.1214 0.01120 0.00472 -0.0978 0.1083 1.0000
6.000 1.1424 0.01149 0.00497 -0.0965 0.0975 1.0000
6.250 1.1570 0.01223 0.00545 -0.0939 0.0547 1.0000
6.500 1.1778 0.01251 0.00574 -0.0926 0.0479 1.0000
6.750 1.1980 0.01284 0.00608 -0.0911 0.0424 1.0000
7.000 1.2182 0.01315 0.00640 -0.0896 0.0377 1.0000
7.250 1.2368 0.01358 0.00677 -0.0878 0.0285 1.0000
7.500 1.2528 0.01415 0.00725 -0.0856 0.0147 1.0000
7.750 1.2716 0.01454 0.00765 -0.0839 0.0123 1.0000
8.000 1.2899 0.01494 0.00809 -0.0821 0.0103 1.0000
8.250 1.3085 0.01532 0.00850 -0.0804 0.0092 1.0000
8.500 1.3260 0.01574 0.00895 -0.0784 0.0081 1.0000
8.750 1.3421 0.01625 0.00949 -0.0762 0.0070 1.0000
9.000 1.3593 0.01665 0.00994 -0.0743 0.0067 1.0000
9.250 1.3761 0.01704 0.01037 -0.0723 0.0062 1.0000
9.500 1.3896 0.01751 0.01089 -0.0696 0.0058 1.0000
9.750 1.4022 0.01794 0.01137 -0.0668 0.0054 1.0000
10.000 1.4131 0.01846 0.01193 -0.0637 0.0050 1.0000
10.250 1.4230 0.01904 0.01258 -0.0604 0.0046 1.0000
10.500 1.4344 0.01957 0.01317 -0.0575 0.0046 1.0000
10.750 1.4461 0.02010 0.01377 -0.0547 0.0043 1.0000
11.000 1.4577 0.02064 0.01436 -0.0520 0.0040 1.0000
11.250 1.4680 0.02128 0.01506 -0.0492 0.0039 1.0000
11.500 1.4785 0.02190 0.01575 -0.0465 0.0038 1.0000
11.750 1.4865 0.02270 0.01663 -0.0434 0.0037 1.0000
12.000 1.4944 0.02351 0.01751 -0.0405 0.0035 1.0000
12.250 1.5009 0.02442 0.01850 -0.0376 0.0034 1.0000
12.500 1.5013 0.02578 0.01995 -0.0339 0.0032 1.0000
12.750 1.5077 0.02678 0.02104 -0.0313 0.0030 1.0000
13.000 1.5136 0.02789 0.02223 -0.0288 0.0030 1.0000
13.250 1.5148 0.02940 0.02385 -0.0261 0.0030 1.0000
13.500 1.5186 0.03082 0.02535 -0.0240 0.0030 1.0000
13.750 1.5195 0.03258 0.02722 -0.0219 0.0029 1.0000
14.000 1.5210 0.03442 0.02916 -0.0202 0.0027 1.0000
14.250 1.5219 0.03644 0.03130 -0.0188 0.0027 1.0000
14.500 1.5180 0.03910 0.03408 -0.0175 0.0027 1.0000
14.750 1.5205 0.04122 0.03629 -0.0168 0.0025 1.0000
15.000 1.5156 0.04428 0.03947 -0.0161 0.0025 1.0000
15.250 1.5092 0.04769 0.04300 -0.0158 0.0025 1.0000
15.500 1.5060 0.05080 0.04621 -0.0157 0.0024 1.0000
15.750 1.4942 0.05517 0.05073 -0.0160 0.0025 1.0000
16.000 1.4850 0.05936 0.05505 -0.0166 0.0025 1.0000
16.250 1.4758 0.06369 0.05948 -0.0174 0.0024 1.0000
16.500 1.4806 0.06608 0.06192 -0.0178 0.0022 1.0000
16.750 1.4534 0.07345 0.06949 -0.0198 0.0024 1.0000
17.000 1.4441 0.07823 0.07438 -0.0212 0.0024 1.0000
17.250 1.4358 0.08295 0.07918 -0.0227 0.0023 1.0000
17.500 1.4199 0.08907 0.08543 -0.0248 0.0022 1.0000
17.750 1.4000 0.09598 0.09249 -0.0273 0.0023 1.0000
18.000 1.3907 0.10118 0.09776 -0.0293 0.0022 1.0000
18.250 1.3742 0.10774 0.10445 -0.0318 0.0022 1.0000
18.500 1.3559 0.11479 0.11161 -0.0347 0.0022 1.0000
18.750 1.3388 0.12169 0.11864 -0.0376 0.0022 1.0000
19.000 1.3205 0.12901 0.12607 -0.0409 0.0023 1.0000
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