GOE 702 AIRFOIL (goe702-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 702 AIRFOIL (goe702-il) Reynolds number: 200,000 Max Cl/Cd: 61.6 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe702-il-200000-n5.txt Download as CSV file: xf-goe702-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 702 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.6390 0.04974 0.04456 -0.0864 0.8086 0.0502
-12.500 -0.6919 0.04041 0.03482 -0.0949 0.7950 0.0502
-12.250 -0.7146 0.03720 0.03132 -0.0940 0.7840 0.0504
-12.000 -0.7263 0.03503 0.02885 -0.0917 0.7753 0.0508
-11.750 -0.7200 0.03360 0.02729 -0.0903 0.7680 0.0513
-11.500 -0.7073 0.03259 0.02624 -0.0891 0.7612 0.0519
-11.250 -0.6939 0.03162 0.02517 -0.0879 0.7553 0.0524
-11.000 -0.6797 0.03060 0.02404 -0.0868 0.7500 0.0531
-10.750 -0.6644 0.02953 0.02283 -0.0858 0.7442 0.0538
-10.500 -0.6487 0.02843 0.02156 -0.0848 0.7386 0.0547
-10.250 -0.6322 0.02734 0.02024 -0.0836 0.7334 0.0555
-10.000 -0.6143 0.02628 0.01894 -0.0826 0.7277 0.0564
-9.750 -0.5943 0.02543 0.01801 -0.0818 0.7214 0.0572
-9.500 -0.5731 0.02478 0.01731 -0.0809 0.7154 0.0580
-9.250 -0.5514 0.02418 0.01660 -0.0800 0.7098 0.0591
-9.000 -0.5290 0.02353 0.01587 -0.0793 0.7030 0.0603
-8.750 -0.5066 0.02284 0.01502 -0.0785 0.6966 0.0617
-8.500 -0.4840 0.02218 0.01416 -0.0777 0.6912 0.0630
-8.250 -0.4602 0.02165 0.01363 -0.0770 0.6857 0.0641
-8.000 -0.4359 0.02116 0.01311 -0.0765 0.6806 0.0655
-7.750 -0.4115 0.02067 0.01252 -0.0758 0.6758 0.0670
-7.500 -0.3868 0.02018 0.01188 -0.0752 0.6714 0.0689
-7.250 -0.3618 0.01974 0.01140 -0.0746 0.6667 0.0706
-7.000 -0.3362 0.01939 0.01104 -0.0742 0.6614 0.0725
-6.750 -0.3104 0.01901 0.01059 -0.0736 0.6565 0.0748
-6.500 -0.2847 0.01862 0.01007 -0.0731 0.6519 0.0771
-6.250 -0.2587 0.01832 0.00976 -0.0726 0.6470 0.0793
-6.000 -0.2322 0.01803 0.00944 -0.0722 0.6412 0.0822
-5.750 -0.2058 0.01771 0.00903 -0.0717 0.6358 0.0853
-5.500 -0.1794 0.01747 0.00875 -0.0713 0.6310 0.0881
-5.250 -0.1524 0.01722 0.00845 -0.0709 0.6256 0.0918
-5.000 -0.1257 0.01695 0.00815 -0.0705 0.6192 0.0953
-4.750 -0.0989 0.01673 0.00789 -0.0700 0.6132 0.0991
-4.500 -0.0717 0.01653 0.00757 -0.0696 0.6073 0.1034
-4.250 -0.0450 0.01626 0.00735 -0.0693 0.6004 0.1073
-4.000 -0.0180 0.01607 0.00710 -0.0689 0.5939 0.1118
-3.750 0.0092 0.01587 0.00683 -0.0685 0.5873 0.1161
-3.500 0.0360 0.01564 0.00663 -0.0681 0.5790 0.1205
-3.250 0.0630 0.01548 0.00638 -0.0677 0.5716 0.1252
-3.000 0.0902 0.01528 0.00619 -0.0673 0.5627 0.1298
-2.750 0.1170 0.01510 0.00599 -0.0669 0.5544 0.1348
-2.500 0.1442 0.01497 0.00581 -0.0666 0.5451 0.1400
-2.250 0.1708 0.01480 0.00562 -0.0661 0.5353 0.1454
-2.000 0.1978 0.01467 0.00549 -0.0657 0.5243 0.1517
-1.750 0.2244 0.01456 0.00532 -0.0653 0.5136 0.1587
-1.500 0.2510 0.01446 0.00521 -0.0649 0.5022 0.1676
-1.250 0.2774 0.01437 0.00512 -0.0645 0.4921 0.1777
-1.000 0.3037 0.01431 0.00504 -0.0640 0.4822 0.1901
-0.750 0.3301 0.01427 0.00501 -0.0636 0.4729 0.2061
-0.500 0.3560 0.01427 0.00500 -0.0631 0.4640 0.2256
-0.250 0.3823 0.01428 0.00503 -0.0626 0.4560 0.2462
0.000 0.4085 0.01434 0.00507 -0.0622 0.4485 0.2650
0.250 0.4346 0.01442 0.00511 -0.0617 0.4425 0.2826
0.500 0.4611 0.01448 0.00519 -0.0613 0.4366 0.2994
0.750 0.4871 0.01456 0.00526 -0.0609 0.4310 0.3144
1.000 0.5128 0.01468 0.00533 -0.0604 0.4258 0.3280
1.250 0.5393 0.01476 0.00543 -0.0600 0.4208 0.3417
1.500 0.5651 0.01484 0.00553 -0.0595 0.4158 0.3559
1.750 0.5908 0.01494 0.00564 -0.0590 0.4112 0.3706
2.000 0.6162 0.01508 0.00575 -0.0585 0.4074 0.3865
2.500 0.6674 0.01522 0.00603 -0.0576 0.3999 0.4265
2.750 0.6918 0.01523 0.00618 -0.0569 0.3960 0.4648
3.000 0.7142 0.01513 0.00631 -0.0559 0.3923 0.5325
3.500 0.8400 0.01486 0.00691 -0.0697 0.3832 1.0000
3.750 0.8635 0.01508 0.00710 -0.0689 0.3799 1.0000
4.000 0.8867 0.01532 0.00730 -0.0680 0.3768 1.0000
4.250 0.9098 0.01557 0.00749 -0.0671 0.3738 1.0000
4.500 0.9327 0.01585 0.00769 -0.0662 0.3709 1.0000
4.750 0.9556 0.01614 0.00791 -0.0653 0.3680 1.0000
5.000 0.9782 0.01637 0.00817 -0.0644 0.3649 1.0000
5.250 1.0007 0.01663 0.00844 -0.0635 0.3618 1.0000
5.500 1.0230 0.01690 0.00870 -0.0626 0.3590 1.0000
5.750 1.0453 0.01718 0.00896 -0.0616 0.3564 1.0000
6.000 1.0675 0.01748 0.00922 -0.0607 0.3539 1.0000
6.250 1.0900 0.01781 0.00948 -0.0598 0.3515 1.0000
6.500 1.1116 0.01812 0.00981 -0.0588 0.3489 1.0000
6.750 1.1325 0.01842 0.01017 -0.0578 0.3460 1.0000
7.000 1.1533 0.01874 0.01051 -0.0567 0.3432 1.0000
7.250 1.1741 0.01906 0.01085 -0.0557 0.3406 1.0000
7.500 1.1949 0.01940 0.01119 -0.0546 0.3383 1.0000
7.750 1.2157 0.01975 0.01152 -0.0536 0.3360 1.0000
8.000 1.2372 0.02012 0.01184 -0.0527 0.3337 1.0000
8.250 1.2560 0.02051 0.01228 -0.0515 0.3312 1.0000
8.500 1.2736 0.02090 0.01276 -0.0501 0.3286 1.0000
8.750 1.2912 0.02131 0.01322 -0.0487 0.3261 1.0000
9.000 1.3079 0.02173 0.01368 -0.0472 0.3237 1.0000
9.250 1.3230 0.02214 0.01412 -0.0455 0.3213 1.0000
9.500 1.3388 0.02256 0.01454 -0.0439 0.3191 1.0000
9.750 1.3569 0.02299 0.01495 -0.0426 0.3169 1.0000
10.000 1.3722 0.02352 0.01551 -0.0411 0.3147 1.0000
10.250 1.3833 0.02415 0.01625 -0.0393 0.3124 1.0000
10.500 1.3948 0.02481 0.01700 -0.0376 0.3098 1.0000
10.750 1.4066 0.02549 0.01775 -0.0361 0.3072 1.0000
11.000 1.4195 0.02617 0.01848 -0.0348 0.3047 1.0000
11.250 1.4343 0.02681 0.01915 -0.0336 0.3026 1.0000
11.500 1.4514 0.02737 0.01969 -0.0328 0.3002 1.0000
11.750 1.4607 0.02829 0.02068 -0.0314 0.2973 1.0000
12.000 1.4645 0.02948 0.02201 -0.0297 0.2937 1.0000
12.250 1.4708 0.03060 0.02322 -0.0284 0.2900 1.0000
12.500 1.4800 0.03159 0.02423 -0.0273 0.2866 1.0000
12.750 1.4947 0.03229 0.02488 -0.0265 0.2834 1.0000
13.000 1.4957 0.03396 0.02671 -0.0253 0.2799 1.0000
13.250 1.4978 0.03564 0.02851 -0.0242 0.2762 1.0000
13.500 1.5024 0.03716 0.03012 -0.0234 0.2726 1.0000
13.750 1.5111 0.03838 0.03133 -0.0226 0.2692 1.0000
14.000 1.5163 0.03995 0.03295 -0.0219 0.2657 1.0000
14.250 1.5110 0.04250 0.03568 -0.0212 0.2613 1.0000
14.500 1.5106 0.04467 0.03793 -0.0206 0.2571 1.0000
14.750 1.5168 0.04626 0.03952 -0.0201 0.2533 1.0000
15.000 1.5148 0.04881 0.04217 -0.0198 0.2496 1.0000
15.250 1.5067 0.05211 0.04564 -0.0197 0.2453 1.0000
15.500 1.5049 0.05480 0.04840 -0.0196 0.2413 1.0000
15.750 1.5103 0.05670 0.05030 -0.0194 0.2377 1.0000
16.000 1.4953 0.06114 0.05492 -0.0198 0.2331 1.0000
16.250 1.4821 0.06552 0.05942 -0.0204 0.2280 1.0000
16.500 1.4825 0.06822 0.06214 -0.0206 0.2238 1.0000
16.750 1.4603 0.07401 0.06809 -0.0218 0.2185 1.0000
17.000 1.4401 0.07971 0.07390 -0.0230 0.2126 1.0000
17.250 1.4412 0.08249 0.07668 -0.0235 0.2078 1.0000
17.500 1.3970 0.09192 0.08631 -0.0262 0.2004 1.0000
17.750 1.4017 0.09426 0.08864 -0.0266 0.1953 1.0000
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