GOE 336 (MVA H.44) AIRFOIL (goe336-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 336 (MVA H.44) AIRFOIL (goe336-il) Reynolds number: 200,000 Max Cl/Cd: 79.53 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe336-il-200000.txt Download as CSV file: xf-goe336-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3111 0.10503 0.10168 -0.0309 1.0000 0.0383
-8.500 -0.3173 0.10326 0.09998 -0.0333 1.0000 0.0385
-8.250 -0.3214 0.10110 0.09789 -0.0350 1.0000 0.0386
-8.000 -0.2974 0.09378 0.09055 -0.0300 1.0000 0.0397
-7.750 -0.2949 0.09123 0.08805 -0.0290 1.0000 0.0405
-7.500 -0.2991 0.08927 0.08617 -0.0276 1.0000 0.0411
-7.250 -0.3059 0.08752 0.08450 -0.0260 1.0000 0.0418
-7.000 -0.3119 0.08577 0.08285 -0.0249 0.9990 0.0426
-6.750 -0.2796 0.08088 0.07790 -0.0341 0.9906 0.0454
-6.500 -0.2326 0.07457 0.07141 -0.0538 0.9761 0.0484
-6.250 -0.2115 0.07017 0.06705 -0.0535 0.9709 0.0497
-6.000 -0.1842 0.06653 0.06338 -0.0570 0.9586 0.0517
-5.750 -0.1528 0.06272 0.05948 -0.0627 0.9435 0.0552
-5.500 -0.1084 0.05797 0.05437 -0.0742 0.9241 0.0594
-5.250 -0.0939 0.05455 0.05098 -0.0731 0.9056 0.0607
-5.000 -0.0751 0.05210 0.04846 -0.0730 0.8854 0.0629
-4.750 -0.0528 0.04960 0.04579 -0.0740 0.8655 0.0664
-4.500 -0.0176 0.04659 0.04226 -0.0784 0.8461 0.0717
-4.250 -0.0030 0.04358 0.03923 -0.0774 0.8283 0.0728
-4.000 0.0152 0.04147 0.03702 -0.0767 0.8116 0.0746
-3.750 0.0367 0.03966 0.03503 -0.0765 0.7958 0.0785
-3.500 0.0685 0.03742 0.03224 -0.0778 0.7816 0.0857
-3.250 0.0874 0.03503 0.02979 -0.0772 0.7675 0.0871
-3.000 0.1089 0.03331 0.02792 -0.0767 0.7540 0.0894
-2.750 0.1422 0.03376 0.02770 -0.0763 0.7410 0.0990
-2.500 0.1613 0.02994 0.02384 -0.0762 0.7289 0.1007
-2.250 0.1834 0.02824 0.02210 -0.0757 0.7164 0.1031
-2.000 0.2083 0.02716 0.02084 -0.0752 0.7047 0.1094
-1.750 0.2399 0.02185 0.01444 -0.0737 0.6967 0.0729
-1.500 0.2663 0.02016 0.01249 -0.0730 0.6853 0.0677
-1.250 0.2931 0.01859 0.01056 -0.0723 0.6752 0.0656
-1.000 0.3204 0.01741 0.00904 -0.0717 0.6659 0.0651
-0.750 0.3476 0.01674 0.00819 -0.0713 0.6552 0.0671
-0.500 0.3751 0.01615 0.00741 -0.0709 0.6463 0.0689
-0.250 0.4025 0.01558 0.00668 -0.0705 0.6375 0.0701
0.000 0.4294 0.01497 0.00601 -0.0701 0.6295 0.0724
0.250 0.4561 0.01463 0.00568 -0.0697 0.6220 0.0769
0.500 0.4829 0.01443 0.00542 -0.0693 0.6148 0.0841
0.750 0.5090 0.01410 0.00518 -0.0688 0.6080 0.1025
1.000 0.5350 0.01391 0.00503 -0.0684 0.6021 0.1416
1.250 0.5611 0.01381 0.00502 -0.0681 0.5952 0.1644
1.500 0.5877 0.01379 0.00498 -0.0678 0.5900 0.1872
1.750 0.6132 0.01369 0.00506 -0.0674 0.5837 0.2269
2.000 0.7066 0.01223 0.00510 -0.0817 0.5755 1.0000
2.250 0.7322 0.01241 0.00521 -0.0812 0.5697 1.0000
2.500 0.7578 0.01258 0.00531 -0.0807 0.5641 1.0000
2.750 0.7837 0.01278 0.00537 -0.0803 0.5592 1.0000
3.000 0.8086 0.01294 0.00555 -0.0797 0.5526 1.0000
3.250 0.8339 0.01308 0.00561 -0.0791 0.5459 1.0000
3.500 0.8586 0.01323 0.00573 -0.0785 0.5383 1.0000
3.750 0.8836 0.01337 0.00580 -0.0778 0.5311 1.0000
4.000 0.9083 0.01355 0.00598 -0.0772 0.5244 1.0000
4.250 0.9329 0.01368 0.00609 -0.0765 0.5169 1.0000
4.500 0.9575 0.01384 0.00623 -0.0759 0.5096 1.0000
4.750 0.9817 0.01396 0.00634 -0.0751 0.5013 1.0000
5.000 1.0058 0.01411 0.00651 -0.0744 0.4934 1.0000
5.250 1.0300 0.01424 0.00663 -0.0736 0.4854 1.0000
5.500 1.0538 0.01440 0.00683 -0.0729 0.4775 1.0000
5.750 1.0779 0.01455 0.00700 -0.0722 0.4703 1.0000
6.000 1.1015 0.01471 0.00723 -0.0714 0.4625 1.0000
6.250 1.1250 0.01484 0.00737 -0.0705 0.4536 1.0000
6.500 1.1473 0.01495 0.00756 -0.0695 0.4425 1.0000
6.750 1.1693 0.01505 0.00772 -0.0684 0.4296 1.0000
7.000 1.1905 0.01515 0.00786 -0.0671 0.4138 1.0000
7.250 1.2112 0.01529 0.00801 -0.0658 0.3953 1.0000
7.500 1.2318 0.01550 0.00823 -0.0645 0.3771 1.0000
7.750 1.2518 0.01574 0.00852 -0.0632 0.3509 1.0000
8.000 1.2676 0.01621 0.00883 -0.0612 0.3040 1.0000
8.250 1.2767 0.01720 0.00947 -0.0584 0.2536 1.0000
8.500 1.2871 0.01821 0.01029 -0.0558 0.2241 1.0000
8.750 1.2982 0.01916 0.01112 -0.0534 0.1999 1.0000
9.000 1.3114 0.01995 0.01187 -0.0514 0.1786 1.0000
9.250 1.3228 0.02081 0.01264 -0.0491 0.1546 1.0000
9.500 1.3307 0.02184 0.01352 -0.0464 0.1329 1.0000
9.750 1.3375 0.02279 0.01441 -0.0434 0.1188 1.0000
10.000 1.3454 0.02366 0.01529 -0.0407 0.1087 1.0000
10.250 1.3531 0.02462 0.01626 -0.0381 0.0967 1.0000
10.500 1.3595 0.02574 0.01738 -0.0357 0.0801 1.0000
10.750 1.3618 0.02723 0.01878 -0.0331 0.0673 1.0000
11.000 1.3642 0.02886 0.02037 -0.0309 0.0601 1.0000
11.250 1.3695 0.03039 0.02197 -0.0292 0.0545 1.0000
11.500 1.3718 0.03230 0.02393 -0.0276 0.0494 1.0000
11.750 1.3789 0.03391 0.02566 -0.0265 0.0427 1.0000
12.000 1.3837 0.03581 0.02765 -0.0254 0.0347 1.0000
12.250 1.3829 0.03836 0.03017 -0.0245 0.0275 1.0000
12.500 1.3825 0.04095 0.03280 -0.0237 0.0251 1.0000
12.750 1.3821 0.04363 0.03556 -0.0230 0.0241 1.0000
13.000 1.3811 0.04643 0.03848 -0.0225 0.0234 1.0000
13.250 1.3790 0.04941 0.04159 -0.0221 0.0228 1.0000
13.500 1.3758 0.05260 0.04491 -0.0218 0.0224 1.0000
13.750 1.3715 0.05596 0.04841 -0.0217 0.0220 1.0000
14.000 1.3660 0.05956 0.05214 -0.0218 0.0217 1.0000
14.250 1.3594 0.06341 0.05612 -0.0220 0.0214 1.0000
14.500 1.3518 0.06749 0.06033 -0.0224 0.0211 1.0000
14.750 1.3434 0.07177 0.06473 -0.0229 0.0208 1.0000
15.000 1.3346 0.07619 0.06927 -0.0236 0.0205 1.0000
15.250 1.3282 0.08031 0.07352 -0.0242 0.0202 1.0000
15.500 1.3230 0.08434 0.07767 -0.0248 0.0200 1.0000
15.750 1.3182 0.08831 0.08175 -0.0254 0.0198 1.0000
16.000 1.3145 0.09212 0.08567 -0.0260 0.0197 1.0000
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Polar data table (+)
Polar graphs
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