GOE 735 AIRFOIL (goe735-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 735 AIRFOIL (goe735-il) Reynolds number: 200,000 Max Cl/Cd: 49.57 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe735-il-200000.txt Download as CSV file: xf-goe735-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 735 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
------ -------- --------- --------- -------- -------- --------
-14.750 -0.2763 0.14355 0.14003 -0.0269 0.9182 0.0911
-14.500 -0.7698 0.05523 0.05076 -0.0769 1.0000 0.0735
-14.250 -0.8203 0.04898 0.04417 -0.0790 1.0000 0.0737
-13.750 -0.6779 0.05327 0.04894 -0.0831 0.9141 0.0779
-13.500 -0.7329 0.04689 0.04209 -0.0841 0.8894 0.0782
-13.250 -0.7656 0.04363 0.03848 -0.0812 0.8722 0.0788
-13.000 -0.7935 0.04122 0.03572 -0.0768 0.8582 0.0797
-12.750 -0.8220 0.03910 0.03319 -0.0711 0.8456 0.0806
-12.500 -0.8295 0.03761 0.03150 -0.0670 0.8346 0.0818
-12.250 -0.8111 0.03729 0.03123 -0.0655 0.8252 0.0831
-12.000 -0.8001 0.03688 0.03081 -0.0632 0.8151 0.0845
-11.750 -0.7941 0.03619 0.02997 -0.0602 0.8062 0.0862
-11.500 -0.7969 0.03491 0.02838 -0.0563 0.7971 0.0883
-11.250 -0.7929 0.03366 0.02687 -0.0531 0.7885 0.0902
-11.000 -0.7707 0.03335 0.02664 -0.0522 0.7798 0.0919
-10.750 -0.7535 0.03295 0.02620 -0.0505 0.7707 0.0941
-10.500 -0.7434 0.03213 0.02514 -0.0478 0.7632 0.0966
-10.250 -0.7348 0.03098 0.02369 -0.0451 0.7540 0.0991
-10.000 -0.7111 0.03053 0.02330 -0.0443 0.7463 0.1011
-9.750 -0.6906 0.03019 0.02296 -0.0431 0.7368 0.1036
-9.500 -0.6748 0.02954 0.02208 -0.0410 0.7285 0.1065
-9.250 -0.6601 0.02863 0.02089 -0.0389 0.7208 0.1091
-9.000 -0.6350 0.02801 0.02037 -0.0385 0.7114 0.1115
-8.750 -0.6136 0.02766 0.01992 -0.0371 0.7043 0.1142
-8.500 -0.5934 0.02714 0.01927 -0.0358 0.6943 0.1173
-8.250 -0.5749 0.02645 0.01830 -0.0340 0.6866 0.1200
-8.000 -0.5488 0.02574 0.01768 -0.0338 0.6780 0.1227
-7.750 -0.5254 0.02534 0.01723 -0.0329 0.6692 0.1256
-7.500 -0.5029 0.02492 0.01662 -0.0317 0.6620 0.1288
-7.250 -0.4817 0.02462 0.01612 -0.0303 0.6523 0.1316
-7.000 -0.4545 0.02357 0.01509 -0.0302 0.6449 0.1348
-6.750 -0.4293 0.02318 0.01469 -0.0296 0.6363 0.1377
-6.500 -0.4047 0.02276 0.01416 -0.0289 0.6282 0.1410
-6.250 -0.3803 0.02240 0.01359 -0.0279 0.6212 0.1439
-6.000 -0.3535 0.02161 0.01278 -0.0277 0.6121 0.1470
-5.750 -0.3266 0.02110 0.01224 -0.0274 0.6051 0.1501
-5.500 -0.3003 0.02074 0.01185 -0.0270 0.5974 0.1534
-5.250 -0.2744 0.02041 0.01141 -0.0264 0.5898 0.1570
-5.000 -0.2480 0.02006 0.01086 -0.0258 0.5836 0.1602
-4.750 -0.2202 0.01944 0.01036 -0.0259 0.5755 0.1641
-4.500 -0.1937 0.01912 0.01000 -0.0254 0.5686 0.1682
-4.250 -0.1673 0.01892 0.00967 -0.0249 0.5628 0.1728
-4.000 -0.1405 0.01853 0.00931 -0.0246 0.5557 0.1773
-3.750 -0.1143 0.01816 0.00897 -0.0242 0.5494 0.1825
-3.500 -0.0882 0.01801 0.00870 -0.0237 0.5439 0.1886
-3.250 -0.0627 0.01770 0.00847 -0.0232 0.5372 0.1952
-3.000 -0.0376 0.01744 0.00825 -0.0226 0.5312 0.2028
-2.750 -0.0121 0.01726 0.00799 -0.0220 0.5262 0.2118
-2.500 0.0118 0.01706 0.00789 -0.0212 0.5210 0.2232
-2.250 0.0353 0.01682 0.00777 -0.0203 0.5153 0.2377
-2.000 0.0586 0.01658 0.00760 -0.0194 0.5102 0.2584
-1.750 0.0810 0.01635 0.00745 -0.0183 0.5056 0.2914
-1.500 0.1002 0.01603 0.00745 -0.0167 0.5006 0.3460
-1.250 0.1167 0.01560 0.00740 -0.0146 0.4957 0.4229
-1.000 0.1289 0.01504 0.00737 -0.0115 0.4916 0.5428
-0.750 0.1470 0.01454 0.00747 -0.0090 0.4878 0.6892
-0.500 0.2034 0.01472 0.00803 -0.0136 0.4823 0.8172
-0.250 0.2581 0.01514 0.00848 -0.0180 0.4762 0.8608
0.000 0.3056 0.01557 0.00879 -0.0210 0.4711 0.8844
0.250 0.3479 0.01613 0.00917 -0.0230 0.4668 0.9004
0.500 0.3856 0.01663 0.00967 -0.0244 0.4622 0.9150
0.750 0.4366 0.01712 0.01010 -0.0283 0.4571 0.9246
1.000 0.4804 0.01747 0.01034 -0.0310 0.4527 0.9349
1.250 0.5247 0.01785 0.01055 -0.0338 0.4486 0.9457
1.500 0.5799 0.01827 0.01095 -0.0389 0.4437 0.9549
1.750 0.6387 0.01860 0.01125 -0.0447 0.4386 0.9682
2.000 0.6876 0.01876 0.01133 -0.0488 0.4344 0.9790
2.250 0.7396 0.01872 0.01115 -0.0536 0.4307 0.9862
2.500 0.7881 0.01882 0.01118 -0.0580 0.4270 0.9945
2.750 0.8296 0.01877 0.01119 -0.0612 0.4227 1.0000
3.000 0.8496 0.01892 0.01133 -0.0602 0.4191 1.0000
3.250 0.8702 0.01905 0.01142 -0.0593 0.4160 1.0000
3.500 0.8916 0.01921 0.01150 -0.0585 0.4133 1.0000
3.750 0.9135 0.01948 0.01166 -0.0578 0.4107 1.0000
4.000 0.9324 0.01982 0.01206 -0.0567 0.4079 1.0000
4.250 0.9506 0.02012 0.01244 -0.0555 0.4048 1.0000
4.500 0.9696 0.02038 0.01273 -0.0543 0.4015 1.0000
4.750 0.9897 0.02058 0.01291 -0.0533 0.3986 1.0000
5.000 1.0109 0.02075 0.01302 -0.0524 0.3959 1.0000
5.250 1.0332 0.02099 0.01318 -0.0516 0.3935 1.0000
5.500 1.0531 0.02147 0.01364 -0.0506 0.3910 1.0000
5.750 1.0679 0.02190 0.01420 -0.0489 0.3882 1.0000
6.000 1.0835 0.02232 0.01470 -0.0473 0.3851 1.0000
6.250 1.1007 0.02266 0.01506 -0.0459 0.3822 1.0000
6.500 1.1200 0.02291 0.01530 -0.0447 0.3795 1.0000
6.750 1.1412 0.02317 0.01550 -0.0437 0.3773 1.0000
7.000 1.1643 0.02349 0.01574 -0.0431 0.3750 1.0000
7.250 1.1785 0.02411 0.01642 -0.0413 0.3724 1.0000
7.500 1.1873 0.02472 0.01717 -0.0388 0.3695 1.0000
7.750 1.1982 0.02526 0.01779 -0.0365 0.3665 1.0000
8.000 1.2120 0.02569 0.01825 -0.0345 0.3638 1.0000
8.250 1.2306 0.02595 0.01848 -0.0332 0.3613 1.0000
8.500 1.2536 0.02615 0.01862 -0.0325 0.3590 1.0000
8.750 1.2800 0.02656 0.01893 -0.0325 0.3567 1.0000
9.000 1.2799 0.02740 0.01993 -0.0287 0.3542 1.0000
9.250 1.2777 0.02826 0.02094 -0.0248 0.3513 1.0000
9.500 1.2792 0.02899 0.02175 -0.0213 0.3485 1.0000
9.750 1.2867 0.02955 0.02234 -0.0186 0.3460 1.0000
10.000 1.3033 0.02988 0.02266 -0.0171 0.3437 1.0000
10.250 1.3311 0.02999 0.02271 -0.0172 0.3416 1.0000
10.500 1.3641 0.03035 0.02297 -0.0181 0.3391 1.0000
10.750 1.3287 0.03177 0.02460 -0.0098 0.3368 1.0000
11.000 1.2847 0.03371 0.02671 -0.0017 0.3339 1.0000
11.250 1.2581 0.03589 0.02901 0.0028 0.3307 1.0000
11.500 1.2595 0.03707 0.03023 0.0048 0.3280 1.0000
11.750 1.2859 0.03706 0.03019 0.0050 0.3259 1.0000
12.000 1.3295 0.03638 0.02943 0.0040 0.3242 1.0000
12.250 1.3476 0.03715 0.03020 0.0047 0.3218 1.0000
12.500 1.0444 0.06329 0.05696 0.0128 0.3056 1.0000
12.750 1.0914 0.06051 0.05416 0.0135 0.3055 1.0000
13.000 1.1428 0.05756 0.05117 0.0141 0.3054 1.0000
13.250 1.2053 0.05380 0.04736 0.0144 0.3054 1.0000
13.500 1.2921 0.04859 0.04203 0.0139 0.3058 1.0000
14.000 0.6897 0.13380 0.12793 -0.0024 0.2414 1.0000
14.250 0.7581 0.12617 0.12027 0.0008 0.2445 1.0000
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