GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 164 (MVA MK.10) AIRFOIL (goe164-il) Reynolds number: 200,000 Max Cl/Cd: 81.39 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe164-il-200000.txt Download as CSV file: xf-goe164-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 164 (MVA MK.10) 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2995 0.11116 0.10785 -0.0281 1.0000 0.0379
-8.250 -0.3062 0.10969 0.10645 -0.0275 1.0000 0.0381
-8.000 -0.3142 0.10819 0.10502 -0.0262 1.0000 0.0382
-7.750 -0.3208 0.10646 0.10337 -0.0249 1.0000 0.0382
-7.500 -0.3050 0.09965 0.09656 -0.0226 1.0000 0.0395
-7.250 -0.3041 0.09751 0.09447 -0.0203 1.0000 0.0401
-7.000 -0.3108 0.09608 0.09311 -0.0176 1.0000 0.0407
-6.750 -0.3198 0.09486 0.09198 -0.0151 1.0000 0.0412
-6.500 -0.3033 0.09160 0.08873 -0.0189 0.9967 0.0428
-6.250 -0.2707 0.08683 0.08394 -0.0276 0.9904 0.0455
-6.000 -0.2099 0.08036 0.07740 -0.0526 0.9794 0.0491
-5.750 -0.1908 0.07419 0.07123 -0.0553 0.9748 0.0504
-5.500 -0.1624 0.07109 0.06811 -0.0570 0.9716 0.0526
-5.250 -0.1298 0.06730 0.06429 -0.0630 0.9627 0.0566
-5.000 -0.0786 0.06038 0.05728 -0.0788 0.9548 0.0637
-4.750 -0.0484 0.05782 0.05470 -0.0810 0.9485 0.0678
-4.500 0.0059 0.05132 0.04806 -0.0953 0.9408 0.0768
-4.250 0.1052 0.02487 0.02005 -0.1290 0.9389 0.0432
-4.000 0.1512 0.02136 0.01581 -0.1337 0.9345 0.0453
-3.750 0.1971 0.01901 0.01288 -0.1373 0.9315 0.0473
-3.500 0.2313 0.01772 0.01122 -0.1381 0.9213 0.0491
-3.250 0.2736 0.01563 0.00901 -0.1411 0.9176 0.0560
-3.000 0.3070 0.01464 0.00785 -0.1416 0.9064 0.0612
-2.750 0.3439 0.01352 0.00671 -0.1431 0.8959 0.0726
-2.500 0.3833 0.01260 0.00584 -0.1449 0.8853 0.0938
-2.250 0.4232 0.01266 0.00600 -0.1466 0.8730 0.1622
-2.000 0.4625 0.01296 0.00612 -0.1483 0.8586 0.1882
-1.750 0.5002 0.01299 0.00604 -0.1499 0.8421 0.2038
-1.500 0.5351 0.01301 0.00584 -0.1509 0.8246 0.2152
-1.250 0.5663 0.01299 0.00575 -0.1513 0.8071 0.2263
-1.000 0.5954 0.01298 0.00564 -0.1513 0.7900 0.2365
-0.750 0.6237 0.01306 0.00550 -0.1510 0.7731 0.2444
-0.500 0.6507 0.01287 0.00524 -0.1506 0.7563 0.2481
-0.250 0.6773 0.01281 0.00507 -0.1500 0.7396 0.2521
0.000 0.7035 0.01278 0.00492 -0.1494 0.7227 0.2568
0.250 0.7295 0.01271 0.00478 -0.1488 0.7066 0.2620
0.500 0.7554 0.01266 0.00471 -0.1481 0.6906 0.2675
0.750 0.7813 0.01266 0.00462 -0.1475 0.6744 0.2733
1.000 0.8069 0.01261 0.00456 -0.1468 0.6579 0.2792
1.250 0.8324 0.01262 0.00453 -0.1461 0.6406 0.2867
1.500 0.8576 0.01263 0.00453 -0.1454 0.6224 0.2954
1.750 0.8826 0.01270 0.00453 -0.1446 0.6033 0.3064
2.000 0.9071 0.01277 0.00457 -0.1437 0.5815 0.3191
2.250 0.9311 0.01289 0.00463 -0.1428 0.5588 0.3354
2.500 0.9550 0.01298 0.00475 -0.1418 0.5350 0.3602
2.750 0.9783 0.01302 0.00484 -0.1409 0.5128 0.4195
3.000 0.9986 0.01227 0.00491 -0.1390 0.4920 1.0000
3.250 1.0228 0.01258 0.00504 -0.1382 0.4725 1.0000
3.500 1.0470 0.01289 0.00524 -0.1374 0.4551 1.0000
3.750 1.0712 0.01321 0.00543 -0.1366 0.4391 1.0000
4.000 1.0955 0.01352 0.00565 -0.1359 0.4248 1.0000
4.250 1.1199 0.01383 0.00590 -0.1352 0.4125 1.0000
4.500 1.1443 0.01416 0.00618 -0.1345 0.4014 1.0000
4.750 1.1683 0.01452 0.00646 -0.1338 0.3919 1.0000
5.000 1.1928 0.01484 0.00677 -0.1331 0.3824 1.0000
5.250 1.2170 0.01520 0.00710 -0.1324 0.3741 1.0000
5.500 1.2410 0.01557 0.00747 -0.1317 0.3657 1.0000
5.750 1.2651 0.01593 0.00784 -0.1310 0.3577 1.0000
6.000 1.2887 0.01633 0.00822 -0.1303 0.3499 1.0000
6.250 1.3125 0.01669 0.00865 -0.1295 0.3419 1.0000
6.500 1.3356 0.01713 0.00907 -0.1287 0.3342 1.0000
6.750 1.3590 0.01749 0.00952 -0.1279 0.3261 1.0000
7.000 1.3815 0.01797 0.00998 -0.1270 0.3182 1.0000
7.250 1.4035 0.01830 0.01044 -0.1260 0.3079 1.0000
7.500 1.4244 0.01868 0.01087 -0.1248 0.2961 1.0000
7.750 1.4444 0.01903 0.01127 -0.1235 0.2825 1.0000
8.000 1.4644 0.01939 0.01168 -0.1221 0.2696 1.0000
8.250 1.4842 0.01977 0.01213 -0.1208 0.2567 1.0000
8.500 1.5036 0.02014 0.01255 -0.1194 0.2398 1.0000
8.750 1.5219 0.02061 0.01305 -0.1179 0.2232 1.0000
9.250 1.5474 0.02220 0.01446 -0.1133 0.1816 1.0000
9.500 1.5554 0.02327 0.01548 -0.1102 0.1636 1.0000
9.750 1.5647 0.02435 0.01651 -0.1074 0.1264 1.0000
10.000 1.5529 0.02690 0.01856 -0.1020 0.0757 1.0000
10.250 1.5525 0.02875 0.02035 -0.0982 0.0441 1.0000
10.500 1.5502 0.03078 0.02226 -0.0945 0.0349 1.0000
10.750 1.5522 0.03252 0.02416 -0.0915 0.0320 1.0000
11.000 1.5513 0.03455 0.02635 -0.0886 0.0300 1.0000
11.250 1.5469 0.03700 0.02895 -0.0858 0.0286 1.0000
11.500 1.5389 0.03999 0.03211 -0.0834 0.0276 1.0000
11.750 1.5286 0.04347 0.03576 -0.0815 0.0268 1.0000
12.000 1.5242 0.04660 0.03906 -0.0803 0.0263 1.0000
12.250 1.5183 0.05006 0.04270 -0.0794 0.0256 1.0000
12.500 1.5115 0.05377 0.04656 -0.0788 0.0249 1.0000
12.750 1.5037 0.05772 0.05066 -0.0784 0.0242 1.0000
13.000 1.4958 0.06181 0.05488 -0.0782 0.0236 1.0000
13.250 1.4875 0.06604 0.05924 -0.0782 0.0232 1.0000
13.500 1.4798 0.07022 0.06353 -0.0782 0.0228 1.0000
13.750 1.4729 0.07432 0.06773 -0.0781 0.0224 1.0000
14.000 1.4674 0.07819 0.07167 -0.0780 0.0220 1.0000
14.250 1.4635 0.08174 0.07529 -0.0775 0.0217 1.0000
14.500 1.4626 0.08469 0.07828 -0.0765 0.0213 1.0000
14.750 1.4667 0.08669 0.08030 -0.0744 0.0209 1.0000
15.000 1.4791 0.08749 0.08113 -0.0705 0.0204 1.0000
15.250 1.4798 0.09073 0.08453 -0.0702 0.0202 1.0000
15.500 1.4765 0.09468 0.08869 -0.0709 0.0200 1.0000
15.750 1.4726 0.09881 0.09302 -0.0717 0.0198 1.0000
16.000 1.4678 0.10318 0.09759 -0.0729 0.0195 1.0000
16.250 1.4627 0.10765 0.10226 -0.0741 0.0192 1.0000
16.500 1.4567 0.11236 0.10717 -0.0755 0.0191 1.0000
16.750 1.4497 0.11735 0.11236 -0.0771 0.0191 1.0000
17.000 1.4413 0.12276 0.11798 -0.0793 0.0191 1.0000
17.250 1.4316 0.12857 0.12399 -0.0819 0.0192 1.0000
17.500 1.4207 0.13481 0.13044 -0.0852 0.0193 1.0000
17.750 1.4087 0.14147 0.13730 -0.0890 0.0194 1.0000
18.000 1.3959 0.14852 0.14454 -0.0932 0.0195 1.0000
18.250 1.3824 0.15602 0.15222 -0.0980 0.0197 1.0000
18.500 1.3683 0.16394 0.16032 -0.1033 0.0199 1.0000
18.750 1.3541 0.17217 0.16870 -0.1088 0.0201 1.0000
19.000 1.3451 0.17923 0.17589 -0.1131 0.0205 1.0000
19.250 1.3350 0.18755 0.18436 -0.1197 0.0207 1.0000
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Polar data table (+)
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