GOE 741 AIRFOIL (goe741-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 741 AIRFOIL (goe741-il) Reynolds number: 200,000 Max Cl/Cd: 61.58 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe741-il-200000.txt Download as CSV file: xf-goe741-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 741 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2893 0.10729 0.10271 -0.0069 0.6501 0.0730
-9.500 -0.2923 0.10397 0.09941 -0.0097 0.6466 0.0759
-9.250 -0.3234 0.09847 0.09400 -0.0169 0.6449 0.0775
-9.000 -0.2995 0.09600 0.09149 -0.0150 0.6393 0.0782
-8.750 -0.2853 0.09356 0.08902 -0.0146 0.6349 0.0790
-8.500 -0.2766 0.09097 0.08639 -0.0150 0.6313 0.0802
-8.250 -0.2726 0.08810 0.08352 -0.0162 0.6277 0.0819
-8.000 -0.2794 0.08447 0.07995 -0.0192 0.6241 0.0844
-7.750 -0.3580 0.07715 0.07257 -0.0283 0.6242 0.0867
-7.500 -0.3362 0.07438 0.06984 -0.0269 0.6193 0.0872
-7.250 -0.3203 0.07218 0.06763 -0.0258 0.6154 0.0880
-7.000 -0.3094 0.06992 0.06533 -0.0253 0.6122 0.0889
-6.750 -0.3009 0.06754 0.06289 -0.0252 0.6092 0.0903
-6.500 -0.2954 0.06460 0.05994 -0.0259 0.6058 0.0926
-6.250 -0.3136 0.05810 0.05304 -0.0283 0.6038 0.0980
-6.000 -0.3501 0.04007 0.03385 -0.0259 0.6040 0.0696
-5.750 -0.3275 0.03905 0.03288 -0.0255 0.5998 0.0705
-5.500 -0.3208 0.03365 0.02684 -0.0229 0.5970 0.0654
-5.250 -0.3108 0.02898 0.02131 -0.0201 0.5944 0.0632
-5.000 -0.2895 0.02724 0.01919 -0.0189 0.5913 0.0634
-4.750 -0.2651 0.02596 0.01774 -0.0182 0.5876 0.0640
-4.500 -0.2397 0.02499 0.01663 -0.0177 0.5837 0.0651
-4.250 -0.2140 0.02409 0.01553 -0.0171 0.5801 0.0667
-4.000 -0.1878 0.02319 0.01435 -0.0164 0.5769 0.0681
-3.750 -0.1610 0.02226 0.01319 -0.0158 0.5739 0.0694
-3.500 -0.1338 0.02162 0.01255 -0.0156 0.5706 0.0710
-3.250 -0.1059 0.02113 0.01208 -0.0155 0.5667 0.0731
-3.000 -0.0780 0.02065 0.01153 -0.0152 0.5631 0.0759
-2.750 -0.0504 0.02012 0.01100 -0.0150 0.5598 0.0791
-2.500 -0.0231 0.01983 0.01069 -0.0146 0.5568 0.0837
-2.250 0.0041 0.01940 0.01020 -0.0142 0.5540 0.0888
-2.000 0.0313 0.01920 0.01001 -0.0139 0.5507 0.0958
-1.750 0.0580 0.01883 0.00978 -0.0137 0.5470 0.1057
-1.500 0.0842 0.01849 0.00953 -0.0133 0.5435 0.1203
-1.250 0.1101 0.01816 0.00930 -0.0128 0.5404 0.1387
-1.000 0.1364 0.01800 0.00922 -0.0123 0.5375 0.1583
-0.750 0.1633 0.01801 0.00922 -0.0119 0.5348 0.1788
-0.500 0.1898 0.01812 0.00939 -0.0116 0.5315 0.2007
-0.250 0.2158 0.01812 0.00954 -0.0113 0.5278 0.2250
0.000 0.2413 0.01803 0.00958 -0.0109 0.5242 0.2535
0.250 0.2666 0.01786 0.00951 -0.0103 0.5209 0.2843
0.750 0.3143 0.01740 0.00933 -0.0085 0.5156 0.3714
1.000 0.5010 0.01692 0.01047 -0.0377 0.5076 0.9862
1.250 0.5687 0.01671 0.01010 -0.0455 0.5024 1.0000
1.500 0.5939 0.01668 0.00993 -0.0448 0.4990 1.0000
1.750 0.6190 0.01682 0.00989 -0.0441 0.4958 1.0000
2.000 0.6442 0.01700 0.01014 -0.0439 0.4911 1.0000
2.250 0.6694 0.01716 0.01029 -0.0435 0.4870 1.0000
2.500 0.6946 0.01723 0.01030 -0.0429 0.4835 1.0000
2.750 0.7199 0.01727 0.01024 -0.0423 0.4805 1.0000
3.000 0.7452 0.01739 0.01022 -0.0417 0.4777 1.0000
3.250 0.7696 0.01767 0.01060 -0.0414 0.4730 1.0000
3.500 0.7941 0.01785 0.01080 -0.0409 0.4686 1.0000
3.750 0.8191 0.01793 0.01084 -0.0404 0.4651 1.0000
4.000 0.8444 0.01795 0.01078 -0.0397 0.4622 1.0000
4.250 0.8697 0.01809 0.01079 -0.0391 0.4594 1.0000
4.500 0.8925 0.01846 0.01132 -0.0387 0.4543 1.0000
4.750 0.9165 0.01864 0.01152 -0.0382 0.4498 1.0000
5.000 0.9414 0.01864 0.01147 -0.0375 0.4462 1.0000
5.250 0.9670 0.01860 0.01132 -0.0368 0.4432 1.0000
5.500 0.9897 0.01892 0.01171 -0.0362 0.4384 1.0000
5.750 1.0125 0.01913 0.01199 -0.0356 0.4332 1.0000
6.000 1.0369 0.01914 0.01196 -0.0349 0.4292 1.0000
6.250 1.0625 0.01909 0.01182 -0.0342 0.4260 1.0000
6.500 1.0839 0.01946 0.01228 -0.0335 0.4210 1.0000
6.750 1.1056 0.01970 0.01259 -0.0327 0.4156 1.0000
7.000 1.1299 0.01969 0.01254 -0.0320 0.4116 1.0000
7.250 1.1556 0.01967 0.01240 -0.0313 0.4081 1.0000
7.500 1.1733 0.02019 0.01310 -0.0302 0.4019 1.0000
7.750 1.1955 0.02028 0.01321 -0.0294 0.3967 1.0000
8.000 1.2205 0.02021 0.01303 -0.0286 0.3926 1.0000
8.250 1.2382 0.02062 0.01355 -0.0274 0.3864 1.0000
8.500 1.2583 0.02081 0.01377 -0.0263 0.3807 1.0000
8.750 1.2821 0.02082 0.01370 -0.0255 0.3763 1.0000
9.000 1.2982 0.02132 0.01429 -0.0241 0.3705 1.0000
9.250 1.3156 0.02164 0.01466 -0.0227 0.3649 1.0000
9.500 1.3380 0.02173 0.01467 -0.0218 0.3603 1.0000
9.750 1.3520 0.02229 0.01532 -0.0201 0.3549 1.0000
10.000 1.3657 0.02273 0.01582 -0.0183 0.3493 1.0000
10.250 1.3860 0.02288 0.01590 -0.0172 0.3444 1.0000
10.500 1.3974 0.02349 0.01657 -0.0151 0.3394 1.0000
10.750 1.4059 0.02412 0.01729 -0.0128 0.3344 1.0000
11.000 1.4212 0.02449 0.01764 -0.0112 0.3300 1.0000
11.250 1.4411 0.02487 0.01796 -0.0101 0.3260 1.0000
11.500 1.4368 0.02590 0.01915 -0.0065 0.3215 1.0000
11.750 1.4357 0.02663 0.01992 -0.0030 0.3173 1.0000
12.000 1.4491 0.02702 0.02026 -0.0013 0.3132 1.0000
12.250 1.4548 0.02785 0.02111 0.0009 0.3091 1.0000
12.500 1.4435 0.02948 0.02288 0.0038 0.3048 1.0000
12.750 1.4490 0.03051 0.02394 0.0053 0.3005 1.0000
13.000 1.4725 0.03064 0.02399 0.0059 0.2964 1.0000
13.250 1.4657 0.03253 0.02600 0.0077 0.2924 1.0000
13.500 1.4585 0.03460 0.02820 0.0092 0.2880 1.0000
13.750 1.4683 0.03557 0.02918 0.0100 0.2837 1.0000
14.000 1.4949 0.03549 0.02900 0.0106 0.2794 1.0000
14.250 1.4714 0.03897 0.03269 0.0118 0.2752 1.0000
14.500 1.4683 0.04108 0.03488 0.0126 0.2705 1.0000
14.750 1.4881 0.04132 0.03507 0.0132 0.2663 1.0000
15.000 1.4864 0.04346 0.03730 0.0138 0.2620 1.0000
15.250 1.4666 0.04725 0.04124 0.0141 0.2572 1.0000
15.500 1.4766 0.04833 0.04232 0.0146 0.2524 1.0000
15.750 1.4944 0.04876 0.04271 0.0152 0.2479 1.0000
16.000 1.4604 0.05429 0.04847 0.0148 0.2428 1.0000
16.250 1.4651 0.05606 0.05026 0.0149 0.2379 1.0000
16.500 1.4880 0.05586 0.04998 0.0156 0.2330 1.0000
16.750 1.4476 0.06275 0.05712 0.0143 0.2273 1.0000
17.000 1.4562 0.06414 0.05848 0.0143 0.2218 1.0000
17.250 1.4523 0.06706 0.06144 0.0140 0.2161 1.0000
17.500 1.4287 0.07256 0.06709 0.0127 0.2104 1.0000
17.750 1.4603 0.07106 0.06542 0.0135 0.2045 1.0000
18.000 1.4148 0.07965 0.07427 0.0112 0.1989 1.0000
18.250 1.4125 0.08267 0.07732 0.0104 0.1931 1.0000
18.500 1.4097 0.08581 0.08048 0.0097 0.1876 1.0000
18.750 1.3824 0.09250 0.08732 0.0077 0.1816 1.0000
19.000 1.4085 0.09157 0.08628 0.0082 0.1764 1.0000
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