GOE 336 (MVA H.44) AIRFOIL (goe336-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 336 (MVA H.44) AIRFOIL (goe336-il) Reynolds number: 500,000 Max Cl/Cd: 107.06 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe336-il-500000.txt Download as CSV file: xf-goe336-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 336 (MVA H.44) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2932 0.09268 0.09057 -0.0280 1.0000 0.0225
-8.000 -0.2934 0.08993 0.08786 -0.0289 1.0000 0.0236
-7.750 -0.2955 0.08666 0.08464 -0.0350 0.9949 0.0242
-7.500 -0.2695 0.08103 0.07897 -0.0456 0.9836 0.0244
-7.250 -0.2541 0.07479 0.07271 -0.0508 0.9704 0.0248
-7.000 -0.2352 0.07181 0.06971 -0.0520 0.9527 0.0253
-6.750 -0.2166 0.06886 0.06668 -0.0542 0.9260 0.0258
-6.500 -0.2020 0.06607 0.06377 -0.0559 0.8910 0.0265
-6.250 -0.1870 0.06316 0.06070 -0.0578 0.8542 0.0274
-6.000 -0.1675 0.05969 0.05701 -0.0612 0.8214 0.0294
-5.750 -0.1339 0.05511 0.05212 -0.0680 0.7962 0.0307
-5.500 -0.1247 0.04995 0.04680 -0.0691 0.7777 0.0315
-5.250 -0.1069 0.04804 0.04477 -0.0692 0.7615 0.0321
-5.000 -0.0868 0.04608 0.04268 -0.0697 0.7478 0.0329
-4.750 -0.0647 0.04381 0.04027 -0.0706 0.7360 0.0342
-4.500 -0.0285 0.04067 0.03679 -0.0731 0.7260 0.0384
-4.250 -0.0126 0.03552 0.03145 -0.0738 0.7167 0.0397
-4.000 0.0088 0.03418 0.03002 -0.0737 0.7069 0.0405
-3.750 0.0316 0.03281 0.02852 -0.0736 0.6971 0.0418
-3.500 0.0564 0.03097 0.02654 -0.0737 0.6873 0.0442
-3.250 0.0826 0.02672 0.02182 -0.0735 0.6793 0.0494
-3.000 0.1061 0.02590 0.02097 -0.0734 0.6687 0.0506
-2.750 0.1307 0.02502 0.02000 -0.0731 0.6580 0.0527
-2.500 0.1624 0.02494 0.01948 -0.0723 0.6475 0.0588
-2.250 0.1787 0.01466 0.00805 -0.0698 0.6406 0.0402
-2.000 0.2054 0.01369 0.00684 -0.0693 0.6293 0.0401
-1.750 0.2322 0.01292 0.00586 -0.0689 0.6180 0.0401
-1.500 0.2592 0.01227 0.00504 -0.0685 0.6063 0.0401
-1.250 0.2861 0.01173 0.00439 -0.0681 0.5949 0.0404
-1.000 0.3129 0.01132 0.00388 -0.0677 0.5845 0.0409
-0.750 0.3395 0.01103 0.00350 -0.0674 0.5746 0.0416
-0.500 0.3663 0.01078 0.00320 -0.0670 0.5652 0.0423
-0.250 0.3929 0.01060 0.00296 -0.0667 0.5570 0.0432
0.000 0.4198 0.01046 0.00279 -0.0664 0.5490 0.0447
0.250 0.4464 0.01038 0.00264 -0.0660 0.5416 0.0464
0.500 0.4734 0.01028 0.00250 -0.0657 0.5337 0.0478
0.750 0.4999 0.01020 0.00238 -0.0654 0.5268 0.0522
1.000 0.5270 0.01012 0.00237 -0.0651 0.5205 0.0652
1.250 0.5540 0.01014 0.00243 -0.0649 0.5152 0.0962
1.500 0.5812 0.01017 0.00247 -0.0647 0.5093 0.1117
1.750 0.6082 0.01018 0.00250 -0.0646 0.5026 0.1242
2.000 0.6349 0.01021 0.00253 -0.0644 0.4959 0.1391
2.500 0.6869 0.01003 0.00267 -0.0638 0.4825 0.2833
2.750 0.7841 0.00875 0.00296 -0.0796 0.4723 1.0000
3.000 0.8095 0.00888 0.00301 -0.0791 0.4662 1.0000
3.250 0.8352 0.00894 0.00307 -0.0786 0.4600 1.0000
3.500 0.8605 0.00906 0.00314 -0.0781 0.4545 1.0000
3.750 0.8860 0.00916 0.00323 -0.0777 0.4494 1.0000
4.000 0.9115 0.00925 0.00332 -0.0772 0.4433 1.0000
4.250 0.9364 0.00939 0.00341 -0.0766 0.4378 1.0000
4.500 0.9619 0.00947 0.00351 -0.0762 0.4315 1.0000
4.750 0.9867 0.00960 0.00361 -0.0756 0.4240 1.0000
5.000 1.0118 0.00970 0.00374 -0.0751 0.4168 1.0000
5.250 1.0361 0.00986 0.00385 -0.0744 0.4072 1.0000
5.500 1.0604 0.00999 0.00396 -0.0738 0.3928 1.0000
5.750 1.0844 0.01016 0.00411 -0.0731 0.3773 1.0000
6.000 1.1081 0.01035 0.00426 -0.0724 0.3570 1.0000
6.250 1.1283 0.01082 0.00450 -0.0712 0.3065 1.0000
7.000 1.1783 0.01318 0.00612 -0.0660 0.1767 1.0000
7.250 1.1949 0.01391 0.00664 -0.0643 0.1395 1.0000
7.500 1.2113 0.01462 0.00718 -0.0626 0.1144 1.0000
7.750 1.2276 0.01529 0.00773 -0.0608 0.0931 1.0000
8.000 1.2389 0.01627 0.00848 -0.0583 0.0601 1.0000
8.250 1.2559 0.01682 0.00901 -0.0566 0.0535 1.0000
8.500 1.2731 0.01733 0.00952 -0.0549 0.0477 1.0000
8.750 1.2908 0.01778 0.00998 -0.0534 0.0418 1.0000
9.000 1.3054 0.01842 0.01055 -0.0514 0.0248 1.0000
9.250 1.3128 0.01945 0.01152 -0.0483 0.0180 1.0000
9.500 1.3245 0.02010 0.01224 -0.0458 0.0164 1.0000
9.750 1.3346 0.02077 0.01298 -0.0431 0.0158 1.0000
10.000 1.3441 0.02154 0.01385 -0.0404 0.0153 1.0000
10.250 1.3527 0.02245 0.01486 -0.0379 0.0148 1.0000
10.500 1.3601 0.02353 0.01605 -0.0355 0.0144 1.0000
10.750 1.3660 0.02480 0.01743 -0.0333 0.0140 1.0000
11.000 1.3702 0.02632 0.01906 -0.0312 0.0136 1.0000
11.250 1.3717 0.02820 0.02105 -0.0292 0.0133 1.0000
11.500 1.3694 0.03061 0.02357 -0.0275 0.0129 1.0000
11.750 1.3632 0.03363 0.02671 -0.0262 0.0126 1.0000
12.000 1.3689 0.03563 0.02879 -0.0256 0.0124 1.0000
12.250 1.3716 0.03799 0.03125 -0.0250 0.0122 1.0000
12.500 1.3720 0.04063 0.03400 -0.0245 0.0120 1.0000
12.750 1.3711 0.04347 0.03694 -0.0241 0.0119 1.0000
13.000 1.3692 0.04645 0.04001 -0.0237 0.0117 1.0000
13.250 1.3666 0.04955 0.04320 -0.0234 0.0116 1.0000
13.500 1.3635 0.05274 0.04648 -0.0232 0.0114 1.0000
13.750 1.3601 0.05599 0.04982 -0.0231 0.0113 1.0000
14.000 1.3571 0.05927 0.05318 -0.0230 0.0112 1.0000
14.250 1.3543 0.06257 0.05656 -0.0230 0.0111 1.0000
14.500 1.3519 0.06584 0.05990 -0.0230 0.0110 1.0000
14.750 1.3501 0.06906 0.06320 -0.0230 0.0109 1.0000
15.000 1.3488 0.07223 0.06644 -0.0230 0.0107 1.0000
15.250 1.3483 0.07526 0.06953 -0.0229 0.0106 1.0000
15.500 1.3486 0.07820 0.07253 -0.0228 0.0105 1.0000
15.750 1.3496 0.08100 0.07539 -0.0227 0.0104 1.0000
16.000 1.3515 0.08368 0.07813 -0.0224 0.0103 1.0000
16.250 1.3544 0.08611 0.08060 -0.0220 0.0102 1.0000
16.500 1.3612 0.08761 0.08209 -0.0206 0.0100 1.0000
16.750 1.4012 0.08347 0.07779 -0.0126 0.0096 1.0000
17.000 1.3859 0.08893 0.08345 -0.0153 0.0095 1.0000
17.250 1.3817 0.09286 0.08753 -0.0164 0.0095 1.0000
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