GOE 601 AIRFOIL (goe601-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 601 AIRFOIL (goe601-il) Reynolds number: 1,000,000 Max Cl/Cd: 91.16 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe601-il-1000000.txt Download as CSV file: xf-goe601-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 601 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -0.9503 0.09903 0.09590 -0.0674 1.0000 0.0199
-19.500 -0.9608 0.09404 0.09083 -0.0699 1.0000 0.0201
-19.250 -0.9697 0.08923 0.08597 -0.0723 1.0000 0.0203
-19.000 -0.9794 0.08445 0.08112 -0.0747 1.0000 0.0205
-18.750 -0.9882 0.07988 0.07648 -0.0769 1.0000 0.0206
-18.500 -0.9966 0.07542 0.07195 -0.0790 1.0000 0.0208
-18.250 -1.0035 0.07127 0.06772 -0.0809 1.0000 0.0210
-18.000 -1.0099 0.06728 0.06366 -0.0826 1.0000 0.0212
-17.750 -1.0192 0.06315 0.05945 -0.0842 1.0000 0.0213
-17.500 -1.0231 0.05969 0.05592 -0.0856 1.0000 0.0216
-17.250 -1.0304 0.05615 0.05229 -0.0867 1.0000 0.0217
-17.000 -1.0351 0.05297 0.04903 -0.0876 1.0000 0.0219
-16.750 -1.0385 0.05007 0.04605 -0.0882 1.0000 0.0222
-16.500 -1.0392 0.04753 0.04343 -0.0887 1.0000 0.0225
-16.250 -1.0464 0.04460 0.04042 -0.0888 1.0000 0.0225
-16.000 -1.0445 0.04255 0.03829 -0.0888 1.0000 0.0227
-15.750 -1.0473 0.04029 0.03596 -0.0884 1.0000 0.0228
-15.500 -1.0630 0.03713 0.03273 -0.0874 1.0000 0.0232
-15.250 -1.0713 0.03478 0.03031 -0.0862 1.0000 0.0233
-15.000 -1.0778 0.03276 0.02824 -0.0848 1.0000 0.0236
-14.750 -1.0838 0.03093 0.02636 -0.0830 1.0000 0.0238
-14.500 -1.0794 0.02941 0.02479 -0.0824 0.9997 0.0241
-14.250 -1.0607 0.02781 0.02313 -0.0843 0.9983 0.0244
-14.000 -1.0383 0.02665 0.02193 -0.0861 0.9968 0.0250
-13.750 -1.0162 0.02546 0.02068 -0.0878 0.9950 0.0255
-13.500 -0.9932 0.02429 0.01943 -0.0896 0.9934 0.0259
-13.250 -0.9725 0.02340 0.01847 -0.0902 0.9909 0.0263
-13.000 -0.9483 0.02266 0.01767 -0.0911 0.9885 0.0266
-12.750 -0.9312 0.02119 0.01612 -0.0919 0.9858 0.0272
-12.500 -0.9089 0.02002 0.01492 -0.0931 0.9838 0.0278
-12.250 -0.8811 0.01919 0.01406 -0.0947 0.9825 0.0284
-12.000 -0.8617 0.01853 0.01337 -0.0942 0.9782 0.0289
-11.750 -0.8360 0.01793 0.01273 -0.0948 0.9753 0.0295
-11.500 -0.8067 0.01733 0.01209 -0.0960 0.9732 0.0302
-11.250 -0.7752 0.01672 0.01143 -0.0976 0.9715 0.0307
-11.000 -0.7403 0.01621 0.01087 -0.0997 0.9701 0.0311
-10.750 -0.7247 0.01529 0.00991 -0.0985 0.9633 0.0320
-10.500 -0.6993 0.01462 0.00921 -0.0988 0.9583 0.0328
-10.250 -0.6722 0.01413 0.00868 -0.0993 0.9532 0.0335
-10.000 -0.6528 0.01374 0.00825 -0.0979 0.9441 0.0342
-9.750 -0.6304 0.01335 0.00781 -0.0972 0.9356 0.0348
-9.500 -0.6079 0.01301 0.00741 -0.0964 0.9254 0.0354
-9.250 -0.5880 0.01274 0.00708 -0.0950 0.9115 0.0359
-9.000 -0.5703 0.01227 0.00652 -0.0933 0.8946 0.0371
-8.750 -0.5502 0.01192 0.00610 -0.0919 0.8781 0.0380
-8.500 -0.5297 0.01165 0.00575 -0.0906 0.8638 0.0390
-8.250 -0.5084 0.01143 0.00545 -0.0894 0.8525 0.0402
-7.750 -0.4654 0.01098 0.00487 -0.0871 0.8357 0.0430
-7.500 -0.4440 0.01074 0.00459 -0.0859 0.8288 0.0452
-7.250 -0.4214 0.01052 0.00434 -0.0850 0.8232 0.0482
-7.000 -0.4006 0.01019 0.00405 -0.0837 0.8178 0.0571
-6.750 -0.3799 0.00985 0.00385 -0.0825 0.8125 0.0818
-6.500 -0.3550 0.00974 0.00374 -0.0820 0.8077 0.0935
-6.250 -0.3304 0.00959 0.00363 -0.0814 0.8036 0.1005
-6.000 -0.3043 0.00953 0.00354 -0.0810 0.7993 0.1038
-5.750 -0.2795 0.00940 0.00338 -0.0805 0.7950 0.1082
-5.500 -0.2540 0.00929 0.00325 -0.0800 0.7907 0.1122
-5.250 -0.2288 0.00916 0.00313 -0.0795 0.7873 0.1154
-5.000 -0.2029 0.00908 0.00302 -0.0791 0.7834 0.1178
-4.750 -0.1781 0.00894 0.00287 -0.0785 0.7786 0.1230
-4.500 -0.1527 0.00883 0.00274 -0.0780 0.7734 0.1285
-4.250 -0.1278 0.00869 0.00261 -0.0774 0.7692 0.1336
-4.000 -0.1037 0.00849 0.00247 -0.0767 0.7646 0.1460
-3.750 -0.0832 0.00805 0.00227 -0.0754 0.7600 0.2061
-3.500 -0.0600 0.00779 0.00216 -0.0746 0.7552 0.2530
-3.250 -0.0358 0.00759 0.00208 -0.0739 0.7510 0.2821
-3.000 -0.0109 0.00743 0.00199 -0.0733 0.7465 0.3063
-2.750 0.0141 0.00729 0.00191 -0.0727 0.7421 0.3298
-2.500 0.0387 0.00714 0.00184 -0.0721 0.7375 0.3585
-2.250 0.0625 0.00693 0.00178 -0.0712 0.7324 0.3960
-2.000 0.0873 0.00681 0.00175 -0.0706 0.7273 0.4298
-1.750 0.1133 0.00677 0.00173 -0.0701 0.7226 0.4498
-1.500 0.1397 0.00673 0.00172 -0.0698 0.7177 0.4648
-1.250 0.1656 0.00668 0.00170 -0.0693 0.7118 0.4791
-1.000 0.1914 0.00666 0.00167 -0.0688 0.7058 0.4903
-0.750 0.2182 0.00665 0.00167 -0.0685 0.7005 0.5003
-0.500 0.2439 0.00660 0.00165 -0.0680 0.6940 0.5092
-0.250 0.2695 0.00662 0.00163 -0.0675 0.6867 0.5170
0.000 0.2955 0.00658 0.00162 -0.0670 0.6794 0.5246
0.250 0.3206 0.00659 0.00161 -0.0664 0.6717 0.5326
0.500 0.3463 0.00657 0.00161 -0.0659 0.6639 0.5408
0.750 0.3708 0.00658 0.00161 -0.0651 0.6552 0.5501
1.000 0.3959 0.00656 0.00162 -0.0645 0.6464 0.5609
1.250 0.4197 0.00659 0.00164 -0.0636 0.6368 0.5727
1.500 0.4442 0.00657 0.00166 -0.0628 0.6270 0.5856
1.750 0.4671 0.00657 0.00169 -0.0618 0.6160 0.6026
2.000 0.4886 0.00659 0.00173 -0.0604 0.6027 0.6265
2.250 0.5096 0.00659 0.00178 -0.0589 0.5882 0.6536
2.750 0.5489 0.00664 0.00192 -0.0554 0.5556 0.7124
3.000 0.5656 0.00669 0.00201 -0.0529 0.5358 0.7471
3.250 0.5800 0.00677 0.00212 -0.0500 0.5095 0.7854
3.500 0.5881 0.00693 0.00227 -0.0458 0.4732 0.8271
3.750 0.5926 0.00722 0.00250 -0.0409 0.4215 0.8747
4.000 0.6122 0.00772 0.00286 -0.0395 0.3666 0.9219
4.250 0.6588 0.00823 0.00324 -0.0440 0.3335 0.9475
4.500 0.7095 0.00865 0.00356 -0.0494 0.3132 0.9603
4.750 0.7492 0.00899 0.00383 -0.0522 0.3000 0.9705
5.000 0.7826 0.00925 0.00406 -0.0536 0.2910 0.9792
5.250 0.8166 0.00952 0.00429 -0.0551 0.2826 0.9848
5.500 0.8515 0.00975 0.00449 -0.0569 0.2749 0.9895
5.750 0.8837 0.01003 0.00472 -0.0581 0.2662 0.9942
6.000 0.9200 0.01025 0.00491 -0.0602 0.2574 0.9975
6.250 0.9558 0.01051 0.00513 -0.0622 0.2484 0.9996
6.500 0.9699 0.01064 0.00525 -0.0596 0.2421 1.0000
6.750 0.9770 0.01083 0.00540 -0.0556 0.2355 1.0000
7.000 0.9894 0.01098 0.00556 -0.0526 0.2291 1.0000
7.250 0.9995 0.01124 0.00576 -0.0492 0.2188 1.0000
7.500 1.0120 0.01150 0.00598 -0.0464 0.2070 1.0000
7.750 1.0234 0.01185 0.00626 -0.0435 0.1923 1.0000
8.000 1.0317 0.01237 0.00664 -0.0401 0.1688 1.0000
8.250 1.0307 0.01332 0.00732 -0.0353 0.1254 1.0000
8.500 1.0140 0.01513 0.00867 -0.0285 0.0515 1.0000
8.750 1.0237 0.01587 0.00933 -0.0258 0.0390 1.0000
9.000 1.0385 0.01640 0.00985 -0.0240 0.0358 1.0000
9.250 1.0533 0.01695 0.01040 -0.0222 0.0342 1.0000
9.500 1.0674 0.01757 0.01103 -0.0204 0.0324 1.0000
9.750 1.0833 0.01810 0.01159 -0.0189 0.0318 1.0000
10.000 1.0991 0.01866 0.01218 -0.0175 0.0311 1.0000
10.250 1.1142 0.01928 0.01282 -0.0160 0.0304 1.0000
10.500 1.1287 0.01996 0.01352 -0.0145 0.0296 1.0000
10.750 1.1416 0.02075 0.01434 -0.0129 0.0289 1.0000
11.000 1.1535 0.02162 0.01525 -0.0113 0.0283 1.0000
11.250 1.1634 0.02266 0.01634 -0.0095 0.0277 1.0000
11.500 1.1772 0.02346 0.01718 -0.0083 0.0274 1.0000
11.750 1.1906 0.02431 0.01807 -0.0070 0.0271 1.0000
12.000 1.2037 0.02519 0.01899 -0.0058 0.0266 1.0000
12.250 1.2151 0.02621 0.02006 -0.0046 0.0263 1.0000
12.500 1.2263 0.02727 0.02116 -0.0033 0.0259 1.0000
12.750 1.2365 0.02842 0.02235 -0.0021 0.0255 1.0000
13.000 1.2457 0.02966 0.02364 -0.0009 0.0250 1.0000
13.250 1.2539 0.03103 0.02505 0.0004 0.0247 1.0000
13.500 1.2597 0.03262 0.02669 0.0016 0.0243 1.0000
13.750 1.2622 0.03452 0.02865 0.0030 0.0240 1.0000
14.000 1.2569 0.03714 0.03136 0.0045 0.0235 1.0000
14.250 1.2621 0.03896 0.03324 0.0054 0.0234 1.0000
14.500 1.2728 0.04033 0.03467 0.0060 0.0232 1.0000
14.750 1.2809 0.04197 0.03636 0.0066 0.0229 1.0000
15.000 1.2858 0.04395 0.03841 0.0072 0.0227 1.0000
15.250 1.2891 0.04615 0.04068 0.0077 0.0225 1.0000
15.500 1.2941 0.04825 0.04284 0.0081 0.0221 1.0000
15.750 1.2964 0.05066 0.04532 0.0084 0.0219 1.0000
16.000 1.2989 0.05311 0.04783 0.0086 0.0216 1.0000
16.250 1.3021 0.05557 0.05035 0.0086 0.0213 1.0000
16.500 1.3015 0.05851 0.05335 0.0086 0.0210 1.0000
16.750 1.2995 0.06166 0.05657 0.0084 0.0210 1.0000
17.000 1.2987 0.06473 0.05970 0.0081 0.0207 1.0000
17.250 1.2959 0.06811 0.06314 0.0077 0.0204 1.0000
17.500 1.2892 0.07201 0.06711 0.0071 0.0202 1.0000
17.750 1.2760 0.07664 0.07182 0.0065 0.0198 1.0000
18.000 1.2747 0.08001 0.07527 0.0058 0.0197 1.0000
18.250 1.2740 0.08338 0.07872 0.0050 0.0196 1.0000
18.500 1.2740 0.08678 0.08221 0.0040 0.0195 1.0000
18.750 1.2724 0.09038 0.08589 0.0029 0.0193 1.0000
19.000 1.2704 0.09409 0.08967 0.0017 0.0190 1.0000
19.250 1.2673 0.09789 0.09355 0.0005 0.0188 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 601 AIRFOIL (goe601-il)