GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il) Reynolds number: 500,000 Max Cl/Cd: 96.13 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe134-il-500000.txt Download as CSV file: xf-goe134-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3827 0.08663 0.08446 -0.0253 1.0000 0.0183
-7.500 -0.3883 0.08415 0.08202 -0.0249 1.0000 0.0184
-7.250 -0.3904 0.08126 0.07917 -0.0258 1.0000 0.0187
-7.000 -0.3930 0.07838 0.07631 -0.0264 1.0000 0.0190
-6.750 -0.3946 0.07539 0.07333 -0.0271 1.0000 0.0193
-6.500 -0.3942 0.07221 0.07015 -0.0279 1.0000 0.0198
-6.250 -0.3564 0.06439 0.06216 -0.0409 0.9971 0.0214
-6.000 -0.3154 0.05645 0.05389 -0.0509 0.9943 0.0216
-5.750 -0.2963 0.05096 0.04838 -0.0543 0.9912 0.0220
-5.500 -0.2691 0.04784 0.04522 -0.0575 0.9883 0.0224
-5.250 -0.2371 0.04446 0.04173 -0.0614 0.9858 0.0231
-5.000 -0.2007 0.04058 0.03766 -0.0658 0.9838 0.0245
-4.750 -0.1558 0.03638 0.03272 -0.0686 0.9796 0.0268
-4.500 -0.1281 0.03103 0.02737 -0.0720 0.9760 0.0276
-4.250 -0.0946 0.02884 0.02510 -0.0746 0.9723 0.0284
-4.000 -0.0640 0.02679 0.02288 -0.0759 0.9650 0.0299
-3.750 -0.0268 0.02646 0.02200 -0.0759 0.9571 0.0331
-3.500 -0.0036 0.02205 0.01745 -0.0766 0.9451 0.0346
-3.250 0.0222 0.02071 0.01604 -0.0764 0.9311 0.0359
-3.000 0.0483 0.01961 0.01475 -0.0759 0.9148 0.0382
-2.750 0.0757 0.01841 0.01308 -0.0751 0.8956 0.0426
-2.500 0.1007 0.01709 0.01173 -0.0747 0.8703 0.0443
-2.250 0.1266 0.01649 0.01094 -0.0742 0.8397 0.0480
-1.250 -0.0539 0.01759 0.01520 -0.0298 0.8725 0.0382
-0.500 0.3212 0.01175 0.00479 -0.0720 0.6908 0.0493
-0.250 0.3496 0.01106 0.00398 -0.0717 0.6772 0.0438
0.000 0.3779 0.01084 0.00368 -0.0716 0.6632 0.0427
0.250 0.4061 0.01061 0.00341 -0.0716 0.6489 0.0423
0.500 0.4343 0.01040 0.00314 -0.0717 0.6341 0.0422
0.750 0.4625 0.01015 0.00285 -0.0718 0.6194 0.0433
1.000 0.4909 0.01003 0.00267 -0.0718 0.6043 0.0435
1.250 0.5192 0.00996 0.00253 -0.0719 0.5884 0.0438
1.500 0.5474 0.00992 0.00243 -0.0720 0.5720 0.0448
1.750 0.5755 0.00993 0.00236 -0.0720 0.5557 0.0465
2.000 0.6036 0.00998 0.00233 -0.0721 0.5401 0.0489
2.250 0.6316 0.01004 0.00233 -0.0721 0.5246 0.0532
2.500 0.6523 0.00789 0.00245 -0.0710 0.5108 1.0000
2.750 0.6802 0.00805 0.00250 -0.0710 0.4953 1.0000
3.000 0.7079 0.00823 0.00257 -0.0710 0.4794 1.0000
3.250 0.7355 0.00841 0.00266 -0.0711 0.4637 1.0000
3.500 0.7632 0.00860 0.00276 -0.0711 0.4485 1.0000
3.750 0.7907 0.00879 0.00289 -0.0711 0.4337 1.0000
4.000 0.8182 0.00899 0.00302 -0.0712 0.4194 1.0000
4.250 0.8456 0.00920 0.00316 -0.0712 0.4048 1.0000
4.500 0.8728 0.00942 0.00331 -0.0712 0.3894 1.0000
4.750 0.9000 0.00965 0.00349 -0.0712 0.3753 1.0000
5.000 0.9272 0.00987 0.00367 -0.0712 0.3632 1.0000
5.250 0.9542 0.01010 0.00386 -0.0712 0.3507 1.0000
5.500 0.9810 0.01034 0.00406 -0.0712 0.3365 1.0000
5.750 1.0078 0.01060 0.00428 -0.0712 0.3245 1.0000
6.000 1.0345 0.01085 0.00450 -0.0711 0.3146 1.0000
6.250 1.0614 0.01106 0.00474 -0.0711 0.3047 1.0000
6.500 1.0879 0.01132 0.00497 -0.0711 0.2933 1.0000
6.750 1.1141 0.01159 0.00522 -0.0710 0.2818 1.0000
7.000 1.1402 0.01187 0.00547 -0.0709 0.2695 1.0000
7.250 1.1663 0.01214 0.00574 -0.0708 0.2561 1.0000
7.500 1.1921 0.01243 0.00602 -0.0706 0.2427 1.0000
7.750 1.2176 0.01275 0.00633 -0.0704 0.2285 1.0000
8.000 1.2424 0.01314 0.00667 -0.0702 0.2115 1.0000
8.250 1.2666 0.01359 0.00706 -0.0698 0.1873 1.0000
8.500 1.2877 0.01438 0.00761 -0.0691 0.1455 1.0000
8.750 1.3076 0.01527 0.00832 -0.0682 0.1140 1.0000
9.000 1.3277 0.01611 0.00903 -0.0673 0.0911 1.0000
9.250 1.3456 0.01713 0.00987 -0.0661 0.0604 1.0000
9.500 1.3591 0.01855 0.01101 -0.0642 0.0268 1.0000
9.750 1.3765 0.01950 0.01196 -0.0628 0.0208 1.0000
10.000 1.3931 0.02046 0.01299 -0.0612 0.0185 1.0000
10.250 1.4100 0.02132 0.01397 -0.0597 0.0174 1.0000
10.500 1.4253 0.02222 0.01498 -0.0580 0.0166 1.0000
10.750 1.4380 0.02324 0.01610 -0.0559 0.0157 1.0000
11.000 1.4465 0.02442 0.01737 -0.0533 0.0150 1.0000
11.250 1.4459 0.02590 0.01896 -0.0492 0.0143 1.0000
11.500 1.4402 0.02783 0.02103 -0.0449 0.0138 1.0000
11.750 1.4462 0.02914 0.02246 -0.0426 0.0136 1.0000
12.000 1.4495 0.03076 0.02420 -0.0403 0.0133 1.0000
12.250 1.4511 0.03266 0.02621 -0.0382 0.0130 1.0000
12.500 1.4514 0.03483 0.02850 -0.0364 0.0127 1.0000
12.750 1.4509 0.03728 0.03108 -0.0351 0.0125 1.0000
13.000 1.4497 0.04003 0.03394 -0.0342 0.0122 1.0000
13.250 1.4478 0.04304 0.03707 -0.0337 0.0120 1.0000
13.500 1.4453 0.04629 0.04044 -0.0335 0.0118 1.0000
13.750 1.4419 0.04973 0.04400 -0.0335 0.0116 1.0000
14.000 1.4377 0.05333 0.04770 -0.0337 0.0114 1.0000
14.250 1.4329 0.05706 0.05154 -0.0339 0.0113 1.0000
14.500 1.4271 0.06091 0.05547 -0.0342 0.0111 1.0000
14.750 1.4207 0.06483 0.05948 -0.0345 0.0109 1.0000
15.000 1.4138 0.06875 0.06348 -0.0344 0.0107 1.0000
15.250 1.4055 0.07248 0.06729 -0.0333 0.0105 1.0000
15.500 1.4007 0.07662 0.07158 -0.0343 0.0103 1.0000
15.750 1.3962 0.08096 0.07606 -0.0358 0.0102 1.0000
16.000 1.3909 0.08537 0.08062 -0.0372 0.0101 1.0000
16.250 1.3853 0.08989 0.08528 -0.0386 0.0100 1.0000
16.500 1.3792 0.09459 0.09012 -0.0402 0.0099 1.0000
16.750 1.3725 0.09947 0.09514 -0.0419 0.0099 1.0000
17.000 1.3648 0.10456 0.10038 -0.0438 0.0098 1.0000
17.250 1.3568 0.10984 0.10580 -0.0459 0.0097 1.0000
17.500 1.3482 0.11537 0.11147 -0.0484 0.0097 1.0000
17.750 1.3389 0.12116 0.11741 -0.0511 0.0096 1.0000
18.000 1.3291 0.12715 0.12354 -0.0541 0.0096 1.0000
18.250 1.3186 0.13344 0.12998 -0.0574 0.0095 1.0000
18.500 1.3077 0.14002 0.13672 -0.0610 0.0095 1.0000
18.750 1.2963 0.14694 0.14378 -0.0651 0.0095 1.0000
19.000 1.2841 0.15429 0.15128 -0.0696 0.0095 1.0000
19.250 1.2713 0.16201 0.15915 -0.0744 0.0096 1.0000
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