GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il) Reynolds number: 200,000 Max Cl/Cd: 77.31 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe137-il-200000-n5.txt Download as CSV file: xf-goe137-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 137 (MVA H.15) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3444 0.08791 0.08464 -0.0281 1.0000 0.0163
-7.750 -0.3445 0.08478 0.08157 -0.0290 1.0000 0.0162
-7.500 -0.3447 0.08147 0.07832 -0.0305 1.0000 0.0162
-7.250 -0.3463 0.07826 0.07517 -0.0317 1.0000 0.0161
-7.000 -0.3278 0.07240 0.06930 -0.0395 0.9928 0.0162
-6.750 -0.3012 0.06592 0.06278 -0.0494 0.9832 0.0171
-6.500 -0.2748 0.06448 0.06131 -0.0521 0.9761 0.0186
-6.250 -0.2461 0.05908 0.05582 -0.0599 0.9655 0.0193
-6.000 -0.2162 0.05273 0.04932 -0.0680 0.9539 0.0196
-5.750 -0.1857 0.04621 0.04258 -0.0750 0.9418 0.0203
-5.500 -0.1528 0.03746 0.03339 -0.0818 0.9297 0.0226
-5.250 -0.1245 0.02778 0.02280 -0.0862 0.9176 0.0245
-5.000 -0.0985 0.02621 0.02106 -0.0868 0.9039 0.0259
-4.750 -0.0722 0.02539 0.02010 -0.0870 0.8889 0.0281
-4.500 -0.0453 0.02278 0.01698 -0.0872 0.8731 0.0304
-4.250 -0.0182 0.02087 0.01455 -0.0871 0.8563 0.0326
-4.000 0.0091 0.02028 0.01357 -0.0866 0.8384 0.0343
-3.750 0.0349 0.01783 0.01065 -0.0864 0.8211 0.0358
-3.500 0.0612 0.01680 0.00939 -0.0861 0.8030 0.0376
-3.250 0.0878 0.01614 0.00852 -0.0858 0.7857 0.0398
-3.000 0.1148 0.01540 0.00753 -0.0853 0.7695 0.0408
-2.750 0.1418 0.01477 0.00669 -0.0850 0.7544 0.0418
-2.500 0.1689 0.01425 0.00598 -0.0846 0.7402 0.0427
-2.250 0.1961 0.01381 0.00538 -0.0843 0.7271 0.0436
-2.000 0.2233 0.01350 0.00494 -0.0840 0.7148 0.0454
-1.750 0.2506 0.01323 0.00453 -0.0838 0.7035 0.0466
-1.500 0.2781 0.01293 0.00415 -0.0836 0.6923 0.0470
-1.250 0.3056 0.01269 0.00382 -0.0835 0.6819 0.0475
-1.000 0.3332 0.01249 0.00352 -0.0833 0.6723 0.0484
-0.750 0.3609 0.01229 0.00324 -0.0832 0.6624 0.0505
-0.500 0.3886 0.01215 0.00304 -0.0831 0.6526 0.0542
-0.250 0.4162 0.01205 0.00288 -0.0829 0.6420 0.0603
0.000 0.4435 0.01186 0.00284 -0.0829 0.6303 0.1136
0.250 0.4709 0.01174 0.00282 -0.0828 0.6183 0.1642
0.500 0.4981 0.01158 0.00282 -0.0828 0.6070 0.2292
1.000 0.5517 0.00988 0.00283 -0.0822 0.5861 1.0000
1.250 0.5793 0.01000 0.00284 -0.0820 0.5755 1.0000
1.500 0.6067 0.01012 0.00287 -0.0819 0.5651 1.0000
1.750 0.6339 0.01026 0.00290 -0.0817 0.5539 1.0000
2.000 0.6610 0.01040 0.00295 -0.0816 0.5417 1.0000
2.250 0.6883 0.01053 0.00302 -0.0814 0.5297 1.0000
2.500 0.7154 0.01068 0.00311 -0.0813 0.5177 1.0000
2.750 0.7424 0.01084 0.00321 -0.0811 0.5059 1.0000
3.000 0.7693 0.01102 0.00332 -0.0809 0.4940 1.0000
3.250 0.7959 0.01121 0.00345 -0.0807 0.4808 1.0000
3.500 0.8224 0.01141 0.00359 -0.0805 0.4668 1.0000
3.750 0.8489 0.01162 0.00376 -0.0803 0.4543 1.0000
4.000 0.8756 0.01183 0.00396 -0.0801 0.4432 1.0000
4.250 0.9019 0.01205 0.00416 -0.0799 0.4316 1.0000
4.500 0.9281 0.01230 0.00438 -0.0797 0.4192 1.0000
4.750 0.9541 0.01256 0.00462 -0.0794 0.4079 1.0000
5.000 0.9802 0.01281 0.00490 -0.0792 0.3973 1.0000
5.250 1.0062 0.01306 0.00518 -0.0790 0.3867 1.0000
5.500 1.0318 0.01335 0.00548 -0.0787 0.3737 1.0000
5.750 1.0568 0.01367 0.00580 -0.0783 0.3572 1.0000
6.000 1.0807 0.01407 0.00613 -0.0778 0.3328 1.0000
6.250 1.1040 0.01454 0.00650 -0.0772 0.3031 1.0000
6.500 1.1269 0.01504 0.00692 -0.0766 0.2716 1.0000
6.750 1.1482 0.01571 0.00743 -0.0759 0.2307 1.0000
7.000 1.1677 0.01659 0.00808 -0.0750 0.1922 1.0000
7.250 1.1863 0.01754 0.00885 -0.0739 0.1645 1.0000
7.500 1.2072 0.01824 0.00952 -0.0731 0.1447 1.0000
7.750 1.2205 0.01969 0.01051 -0.0715 0.0768 1.0000
8.000 1.2293 0.02156 0.01202 -0.0693 0.0237 1.0000
8.250 1.2459 0.02258 0.01312 -0.0678 0.0189 1.0000
8.500 1.2635 0.02345 0.01413 -0.0664 0.0169 1.0000
8.750 1.2795 0.02440 0.01524 -0.0649 0.0152 1.0000
9.000 1.2936 0.02545 0.01646 -0.0632 0.0142 1.0000
9.250 1.3049 0.02665 0.01783 -0.0612 0.0134 1.0000
9.500 1.3111 0.02798 0.01933 -0.0584 0.0128 1.0000
9.750 1.3134 0.02962 0.02114 -0.0556 0.0123 1.0000
10.000 1.3108 0.03174 0.02342 -0.0528 0.0117 1.0000
10.250 1.3097 0.03392 0.02573 -0.0505 0.0113 1.0000
10.500 1.3149 0.03570 0.02768 -0.0491 0.0108 1.0000
10.750 1.3179 0.03781 0.02993 -0.0479 0.0104 1.0000
11.000 1.3185 0.04027 0.03253 -0.0468 0.0101 1.0000
11.250 1.3185 0.04295 0.03533 -0.0459 0.0099 1.0000
11.500 1.3183 0.04575 0.03825 -0.0452 0.0097 1.0000
11.750 1.3181 0.04863 0.04124 -0.0446 0.0095 1.0000
12.000 1.3177 0.05156 0.04429 -0.0441 0.0093 1.0000
12.250 1.3176 0.05453 0.04737 -0.0436 0.0091 1.0000
12.500 1.3175 0.05751 0.05047 -0.0432 0.0089 1.0000
12.750 1.3175 0.06051 0.05358 -0.0427 0.0088 1.0000
13.000 1.3177 0.06353 0.05671 -0.0423 0.0086 1.0000
13.250 1.3174 0.06664 0.05993 -0.0420 0.0085 1.0000
13.500 1.3166 0.06984 0.06322 -0.0419 0.0083 1.0000
13.750 1.3156 0.07310 0.06657 -0.0418 0.0081 1.0000
14.000 1.3151 0.07630 0.06987 -0.0412 0.0078 1.0000
14.250 1.3127 0.07994 0.07362 -0.0409 0.0076 1.0000
14.500 1.3071 0.08423 0.07813 -0.0422 0.0075 1.0000
14.750 1.3009 0.08878 0.08289 -0.0436 0.0073 1.0000
15.000 1.2941 0.09357 0.08789 -0.0452 0.0072 1.0000
15.250 1.2868 0.09854 0.09305 -0.0469 0.0071 1.0000
15.500 1.2786 0.10381 0.09852 -0.0489 0.0071 1.0000
15.750 1.2696 0.10942 0.10431 -0.0512 0.0071 1.0000
16.000 1.2601 0.11530 0.11038 -0.0539 0.0070 1.0000
16.250 1.2497 0.12155 0.11682 -0.0571 0.0070 1.0000
16.500 1.2389 0.12809 0.12354 -0.0606 0.0070 1.0000
16.750 1.2280 0.13492 0.13055 -0.0644 0.0070 1.0000
17.000 1.2169 0.14209 0.13789 -0.0686 0.0070 1.0000
17.250 1.2057 0.14957 0.14553 -0.0732 0.0070 1.0000
17.500 1.1944 0.15741 0.15353 -0.0782 0.0071 1.0000
17.750 1.1832 0.16558 0.16184 -0.0834 0.0071 1.0000
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