GOE 311 (MVA H.43) AIRFOIL (goe311-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 311 (MVA H.43) AIRFOIL (goe311-il) Reynolds number: 200,000 Max Cl/Cd: 81.96 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe311-il-200000-n5.txt Download as CSV file: xf-goe311-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 311 (MVA H.43) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2871 0.10607 0.10279 -0.0285 1.0000 0.0159
-9.000 -0.2805 0.10300 0.09976 -0.0295 1.0000 0.0156
-8.750 -0.2730 0.09968 0.09646 -0.0315 0.9896 0.0153
-8.500 -0.2614 0.09578 0.09257 -0.0349 0.9743 0.0150
-8.250 -0.2514 0.09195 0.08873 -0.0380 0.9601 0.0148
-8.000 -0.2441 0.08829 0.08508 -0.0405 0.9455 0.0146
-7.750 -0.2393 0.08481 0.08160 -0.0424 0.9295 0.0145
-7.500 -0.2352 0.08129 0.07809 -0.0447 0.9131 0.0145
-7.250 -0.2274 0.07730 0.07408 -0.0481 0.8969 0.0148
-7.000 -0.2177 0.07292 0.06966 -0.0520 0.8806 0.0154
-6.750 -0.2058 0.06809 0.06477 -0.0564 0.8644 0.0158
-6.500 -0.1913 0.06305 0.05964 -0.0609 0.8485 0.0159
-6.250 -0.1741 0.05732 0.05379 -0.0662 0.8328 0.0160
-6.000 -0.1536 0.04970 0.04596 -0.0730 0.8181 0.0162
-5.750 -0.1291 0.02287 0.01739 -0.0906 0.8103 0.0167
-5.500 -0.1036 0.02005 0.01408 -0.0911 0.7962 0.0182
-5.250 -0.0775 0.01861 0.01232 -0.0910 0.7821 0.0207
-5.000 -0.0509 0.01760 0.01105 -0.0909 0.7684 0.0237
-4.750 -0.0237 0.01728 0.01056 -0.0906 0.7546 0.0281
-4.500 0.0040 0.01677 0.00964 -0.0903 0.7411 0.0365
-4.250 0.0315 0.01690 0.00957 -0.0901 0.7276 0.0429
-4.000 0.0586 0.01653 0.00896 -0.0900 0.7146 0.0473
-3.750 0.0860 0.01638 0.00867 -0.0899 0.7018 0.0524
-3.500 0.1136 0.01607 0.00806 -0.0898 0.6891 0.0566
-3.250 0.1406 0.01551 0.00740 -0.0898 0.6763 0.0608
-3.000 0.1682 0.01513 0.00685 -0.0897 0.6629 0.0631
-2.750 0.1958 0.01471 0.00624 -0.0896 0.6491 0.0639
-2.500 0.2235 0.01437 0.00570 -0.0894 0.6356 0.0647
-2.250 0.2511 0.01408 0.00526 -0.0893 0.6230 0.0655
-2.000 0.2787 0.01384 0.00488 -0.0891 0.6116 0.0664
-1.750 0.3064 0.01365 0.00455 -0.0890 0.6017 0.0678
-1.500 0.3339 0.01348 0.00427 -0.0889 0.5930 0.0696
-1.250 0.3616 0.01334 0.00406 -0.0888 0.5849 0.0715
-1.000 0.3891 0.01324 0.00388 -0.0887 0.5785 0.0738
-0.750 0.4169 0.01316 0.00376 -0.0886 0.5726 0.0771
-0.500 0.4445 0.01312 0.00372 -0.0885 0.5672 0.0839
-0.250 0.4722 0.01313 0.00372 -0.0885 0.5623 0.0999
0.000 0.5001 0.01318 0.00374 -0.0885 0.5575 0.1149
0.250 0.5278 0.01325 0.00375 -0.0884 0.5532 0.1248
0.500 0.5555 0.01337 0.00375 -0.0884 0.5494 0.1335
0.750 0.5834 0.01343 0.00384 -0.0884 0.5452 0.1422
1.000 0.6111 0.01353 0.00388 -0.0884 0.5411 0.1491
1.250 0.6386 0.01359 0.00394 -0.0884 0.5374 0.1543
1.500 0.6661 0.01369 0.00400 -0.0884 0.5339 0.1592
1.750 0.6938 0.01375 0.00407 -0.0884 0.5299 0.1635
2.000 0.7212 0.01379 0.00416 -0.0884 0.5259 0.1683
2.250 0.7486 0.01390 0.00426 -0.0884 0.5222 0.1768
2.500 0.7759 0.01399 0.00439 -0.0884 0.5186 0.1863
2.750 0.8031 0.01403 0.00452 -0.0884 0.5136 0.1949
3.000 0.8300 0.01410 0.00462 -0.0882 0.5077 0.2027
3.250 0.8566 0.01418 0.00474 -0.0881 0.5004 0.2123
3.500 0.8830 0.01423 0.00484 -0.0879 0.4916 0.2282
3.750 0.9094 0.01426 0.00496 -0.0877 0.4821 0.2577
4.000 0.9356 0.01428 0.00509 -0.0875 0.4743 0.3171
4.250 0.9653 0.01318 0.00525 -0.0879 0.4677 1.0000
4.500 0.9918 0.01334 0.00541 -0.0877 0.4624 1.0000
4.750 1.0181 0.01351 0.00559 -0.0875 0.4573 1.0000
5.000 1.0445 0.01365 0.00579 -0.0874 0.4507 1.0000
5.250 1.0705 0.01382 0.00597 -0.0871 0.4445 1.0000
5.500 1.0967 0.01397 0.00622 -0.0869 0.4370 1.0000
5.750 1.1224 0.01414 0.00642 -0.0867 0.4296 1.0000
6.000 1.1484 0.01431 0.00668 -0.0864 0.4210 1.0000
6.250 1.1738 0.01450 0.00692 -0.0861 0.4122 1.0000
6.500 1.1990 0.01469 0.00721 -0.0858 0.4016 1.0000
6.750 1.2229 0.01492 0.00744 -0.0853 0.3820 1.0000
7.000 1.2427 0.01538 0.00771 -0.0842 0.3417 1.0000
7.250 1.2596 0.01617 0.00824 -0.0827 0.2967 1.0000
7.500 1.2756 0.01709 0.00894 -0.0813 0.2553 1.0000
7.750 1.2899 0.01814 0.00979 -0.0796 0.2150 1.0000
8.000 1.3035 0.01921 0.01069 -0.0779 0.1809 1.0000
8.250 1.3133 0.02053 0.01175 -0.0757 0.1336 1.0000
8.500 1.3118 0.02255 0.01336 -0.0721 0.0809 1.0000
8.750 1.3205 0.02365 0.01447 -0.0696 0.0650 1.0000
9.000 1.3164 0.02553 0.01611 -0.0658 0.0243 1.0000
9.250 1.3225 0.02688 0.01754 -0.0633 0.0194 1.0000
9.500 1.3300 0.02820 0.01900 -0.0613 0.0176 1.0000
9.750 1.3358 0.02973 0.02067 -0.0593 0.0162 1.0000
10.000 1.3393 0.03155 0.02263 -0.0574 0.0149 1.0000
10.250 1.3397 0.03377 0.02506 -0.0556 0.0136 1.0000
10.500 1.3408 0.03607 0.02752 -0.0542 0.0128 1.0000
10.750 1.3436 0.03832 0.02993 -0.0532 0.0124 1.0000
11.000 1.3444 0.04089 0.03265 -0.0523 0.0120 1.0000
11.250 1.3436 0.04371 0.03562 -0.0516 0.0117 1.0000
11.500 1.3417 0.04676 0.03881 -0.0510 0.0113 1.0000
11.750 1.3386 0.04999 0.04218 -0.0505 0.0110 1.0000
12.000 1.3352 0.05334 0.04566 -0.0502 0.0107 1.0000
12.250 1.3317 0.05675 0.04919 -0.0500 0.0104 1.0000
12.500 1.3283 0.06020 0.05275 -0.0499 0.0101 1.0000
12.750 1.3246 0.06375 0.05639 -0.0499 0.0097 1.0000
13.000 1.3204 0.06741 0.06015 -0.0499 0.0094 1.0000
13.250 1.3149 0.07122 0.06403 -0.0499 0.0091 1.0000
13.500 1.3085 0.07505 0.06791 -0.0497 0.0088 1.0000
13.750 1.3073 0.07828 0.07122 -0.0494 0.0086 1.0000
14.000 1.3086 0.08126 0.07433 -0.0493 0.0084 1.0000
14.250 1.3102 0.08418 0.07736 -0.0490 0.0083 1.0000
14.500 1.3122 0.08705 0.08035 -0.0487 0.0081 1.0000
14.750 1.3146 0.08989 0.08330 -0.0484 0.0079 1.0000
15.000 1.3169 0.09275 0.08627 -0.0481 0.0078 1.0000
15.250 1.3191 0.09566 0.08930 -0.0479 0.0076 1.0000
15.500 1.3206 0.09873 0.09251 -0.0478 0.0075 1.0000
15.750 1.3208 0.10211 0.09604 -0.0480 0.0074 1.0000
16.000 1.3198 0.10580 0.09988 -0.0486 0.0072 1.0000
16.250 1.3176 0.10976 0.10400 -0.0495 0.0071 1.0000
16.500 1.3148 0.11389 0.10827 -0.0507 0.0069 1.0000
16.750 1.3116 0.11815 0.11268 -0.0521 0.0067 1.0000
17.000 1.3084 0.12246 0.11712 -0.0537 0.0066 1.0000
17.250 1.3040 0.12713 0.12194 -0.0557 0.0065 1.0000
17.500 1.2994 0.13192 0.12686 -0.0579 0.0063 1.0000
17.750 1.2944 0.13687 0.13194 -0.0602 0.0062 1.0000
18.000 1.2893 0.14189 0.13708 -0.0627 0.0061 1.0000
18.250 1.2828 0.14738 0.14272 -0.0656 0.0061 1.0000
18.500 1.2755 0.15318 0.14866 -0.0688 0.0060 1.0000
18.750 1.2665 0.15979 0.15542 -0.0728 0.0059 1.0000
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