GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.72 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe134-il-1000000.txt Download as CSV file: xf-goe134-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 134 (MVA H.12) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3930 0.08688 0.08534 -0.0271 1.0000 0.0139
-7.750 -0.4017 0.08365 0.08214 -0.0279 1.0000 0.0139
-7.500 -0.4074 0.08036 0.07887 -0.0288 1.0000 0.0139
-7.000 -0.3718 0.06770 0.06614 -0.0436 0.9956 0.0142
-6.750 -0.3489 0.06432 0.06272 -0.0477 0.9941 0.0144
-6.500 -0.3252 0.06061 0.05897 -0.0523 0.9911 0.0148
-6.250 -0.2980 0.05643 0.05472 -0.0577 0.9884 0.0153
-6.000 -0.2586 0.04882 0.04686 -0.0661 0.9854 0.0173
-5.750 -0.2295 0.04275 0.04055 -0.0700 0.9811 0.0174
-5.500 -0.2107 0.03641 0.03398 -0.0725 0.9744 0.0178
-5.250 -0.1871 0.03473 0.03225 -0.0734 0.9680 0.0181
-5.000 -0.1648 0.03303 0.03045 -0.0736 0.9586 0.0185
-4.750 -0.1419 0.03109 0.02839 -0.0736 0.9477 0.0192
-4.500 -0.1112 0.02808 0.02489 -0.0725 0.9361 0.0216
-4.250 -0.0902 0.02267 0.01900 -0.0724 0.9230 0.0220
-4.000 -0.0665 0.02127 0.01752 -0.0722 0.9056 0.0224
-3.750 -0.0419 0.02026 0.01638 -0.0720 0.8838 0.0228
-3.500 -0.0167 0.01933 0.01526 -0.0717 0.8534 0.0236
-3.250 0.0116 0.01965 0.01520 -0.0706 0.8111 0.0265
-3.000 0.0386 0.01890 0.01403 -0.0702 0.7727 0.0267
-2.500 0.0925 0.01464 0.00926 -0.0706 0.7299 0.0282
-2.250 0.1205 0.01399 0.00850 -0.0708 0.7143 0.0290
-2.000 0.1488 0.01356 0.00792 -0.0709 0.7005 0.0308
-1.750 0.1779 0.01427 0.00848 -0.0707 0.6869 0.0330
-1.500 0.2062 0.01219 0.00621 -0.0710 0.6745 0.0349
-1.250 0.2346 0.01164 0.00564 -0.0712 0.6617 0.0361
-1.000 0.2631 0.01127 0.00521 -0.0713 0.6487 0.0378
-0.750 0.2918 0.01111 0.00498 -0.0714 0.6351 0.0400
0.000 -1.2020 0.02142 0.01879 0.2505 0.6726 0.0347
0.250 0.4063 0.00955 0.00308 -0.0714 0.5766 0.0329
0.500 0.4347 0.00928 0.00275 -0.0715 0.5606 0.0328
0.750 0.4632 0.00912 0.00253 -0.0717 0.5451 0.0328
1.000 0.4917 0.00899 0.00235 -0.0719 0.5306 0.0328
1.250 0.5202 0.00899 0.00230 -0.0720 0.5164 0.0332
1.500 0.5488 0.00889 0.00213 -0.0722 0.5025 0.0334
1.750 0.5773 0.00882 0.00200 -0.0724 0.4884 0.0338
2.000 0.6058 0.00881 0.00192 -0.0726 0.4738 0.0351
2.250 0.6342 0.00884 0.00190 -0.0727 0.4590 0.0367
2.500 0.6626 0.00890 0.00190 -0.0729 0.4445 0.0383
2.750 0.6908 0.00898 0.00193 -0.0730 0.4304 0.0401
3.000 0.7190 0.00907 0.00198 -0.0732 0.4164 0.0478
3.250 0.7401 0.00708 0.00217 -0.0723 0.4042 1.0000
3.500 0.7682 0.00724 0.00225 -0.0725 0.3903 1.0000
3.750 0.7961 0.00743 0.00235 -0.0726 0.3742 1.0000
4.000 0.8240 0.00762 0.00246 -0.0727 0.3595 1.0000
4.250 0.8520 0.00778 0.00257 -0.0729 0.3484 1.0000
4.500 0.8798 0.00796 0.00270 -0.0730 0.3363 1.0000
4.750 0.9074 0.00815 0.00284 -0.0731 0.3233 1.0000
5.000 0.9350 0.00836 0.00298 -0.0732 0.3101 1.0000
5.250 0.9625 0.00855 0.00313 -0.0733 0.2995 1.0000
5.500 0.9903 0.00871 0.00328 -0.0734 0.2909 1.0000
5.750 1.0176 0.00892 0.00345 -0.0735 0.2788 1.0000
6.000 1.0447 0.00915 0.00362 -0.0735 0.2665 1.0000
6.250 1.0719 0.00937 0.00381 -0.0736 0.2560 1.0000
6.500 1.0990 0.00958 0.00400 -0.0736 0.2451 1.0000
6.750 1.1258 0.00983 0.00421 -0.0736 0.2317 1.0000
7.000 1.1524 0.01009 0.00443 -0.0736 0.2194 1.0000
7.250 1.1785 0.01040 0.00468 -0.0736 0.2030 1.0000
7.500 1.2038 0.01081 0.00499 -0.0734 0.1802 1.0000
7.750 1.2268 0.01149 0.00544 -0.0729 0.1413 1.0000
8.000 1.2494 0.01219 0.00597 -0.0724 0.1108 1.0000
8.250 1.2723 0.01284 0.00649 -0.0719 0.0875 1.0000
8.500 1.2941 0.01358 0.00706 -0.0712 0.0620 1.0000
8.750 1.3125 0.01469 0.00790 -0.0700 0.0271 1.0000
9.000 1.3332 0.01548 0.00865 -0.0691 0.0167 1.0000
9.250 1.3550 0.01611 0.00932 -0.0683 0.0145 1.0000
9.500 1.3771 0.01667 0.00994 -0.0675 0.0135 1.0000
9.750 1.3990 0.01721 0.01054 -0.0668 0.0127 1.0000
10.000 1.4197 0.01783 0.01122 -0.0659 0.0119 1.0000
10.250 1.4381 0.01863 0.01209 -0.0646 0.0110 1.0000
10.500 1.4537 0.01962 0.01319 -0.0629 0.0103 1.0000
10.750 1.4728 0.02023 0.01386 -0.0618 0.0101 1.0000
11.000 1.4902 0.02093 0.01462 -0.0604 0.0097 1.0000
11.250 1.5055 0.02170 0.01547 -0.0587 0.0093 1.0000
11.500 1.5189 0.02252 0.01636 -0.0567 0.0089 1.0000
11.750 1.5293 0.02341 0.01732 -0.0543 0.0086 1.0000
12.000 1.5347 0.02443 0.01842 -0.0510 0.0084 1.0000
12.250 1.5373 0.02574 0.01982 -0.0478 0.0082 1.0000
12.500 1.5336 0.02762 0.02181 -0.0442 0.0079 1.0000
12.750 1.5207 0.03042 0.02478 -0.0403 0.0077 1.0000
13.000 1.5297 0.03175 0.02618 -0.0390 0.0076 1.0000
13.250 1.5364 0.03334 0.02787 -0.0378 0.0074 1.0000
13.500 1.5407 0.03530 0.02992 -0.0368 0.0072 1.0000
13.750 1.5421 0.03773 0.03246 -0.0360 0.0071 1.0000
14.000 1.5418 0.04053 0.03537 -0.0356 0.0070 1.0000
14.250 1.5403 0.04368 0.03863 -0.0356 0.0068 1.0000
14.500 1.5379 0.04708 0.04214 -0.0358 0.0067 1.0000
14.750 1.5334 0.05081 0.04599 -0.0362 0.0066 1.0000
15.000 1.5275 0.05484 0.05013 -0.0369 0.0065 1.0000
15.250 1.5207 0.05909 0.05449 -0.0378 0.0064 1.0000
15.500 1.5123 0.06362 0.05914 -0.0388 0.0063 1.0000
15.750 1.5033 0.06838 0.06401 -0.0400 0.0063 1.0000
16.000 1.4934 0.07337 0.06910 -0.0414 0.0062 1.0000
16.250 1.4825 0.07857 0.07441 -0.0429 0.0062 1.0000
16.500 1.4717 0.08390 0.07984 -0.0446 0.0061 1.0000
16.750 1.4608 0.08934 0.08538 -0.0464 0.0060 1.0000
17.000 1.4496 0.09488 0.09102 -0.0483 0.0060 1.0000
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Polar data table (+)
Polar graphs
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