GOE 140 (MVA H.17) AIRFOIL (goe140-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 140 (MVA H.17) AIRFOIL (goe140-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.03 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe140-il-1000000-n5.txt Download as CSV file: xf-goe140-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 140 (MVA H.17) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3291 0.09357 0.09191 -0.0215 0.9075 0.0076
-8.500 -0.3367 0.08749 0.08568 -0.0242 0.8674 0.0087
-8.250 -0.3294 0.08505 0.08311 -0.0257 0.8359 0.0089
-8.000 -0.3206 0.08261 0.08058 -0.0276 0.8127 0.0090
-7.750 -0.3074 0.07980 0.07769 -0.0308 0.7940 0.0092
-7.500 -0.2929 0.07670 0.07453 -0.0345 0.7767 0.0095
-7.250 -0.2771 0.07308 0.07084 -0.0391 0.7601 0.0100
-7.000 -0.2606 0.06472 0.06238 -0.0499 0.7475 0.0117
-6.750 -0.2389 0.06231 0.05987 -0.0533 0.7291 0.0119
-6.500 -0.2163 0.05971 0.05717 -0.0569 0.7099 0.0122
-6.250 -0.1924 0.05680 0.05415 -0.0608 0.6913 0.0126
-6.000 -0.1590 0.04644 0.04354 -0.0731 0.6788 0.0152
-5.750 -0.1332 0.04440 0.04136 -0.0754 0.6598 0.0155
-5.500 -0.1069 0.04254 0.03937 -0.0774 0.6409 0.0157
-5.250 -0.0800 0.04064 0.03733 -0.0793 0.6239 0.0161
-5.000 -0.0526 0.03870 0.03525 -0.0812 0.6078 0.0166
-4.750 -0.0233 0.03593 0.03229 -0.0836 0.5920 0.0174
-4.500 0.0133 0.02896 0.02489 -0.0879 0.5800 0.0195
-4.250 0.0445 0.02426 0.01979 -0.0903 0.5666 0.0203
-4.000 0.0732 0.02249 0.01780 -0.0912 0.5506 0.0206
-3.750 0.1022 0.02072 0.01578 -0.0920 0.5337 0.0208
-3.500 0.1312 0.01925 0.01408 -0.0926 0.5160 0.0212
-3.250 0.1599 0.01826 0.01289 -0.0931 0.4977 0.0216
-3.000 0.1900 0.01597 0.01025 -0.0938 0.4802 0.0223
-2.500 0.2485 0.01323 0.00696 -0.0947 0.4505 0.0237
-2.250 0.2773 0.01254 0.00608 -0.0950 0.4379 0.0240
-2.000 0.3061 0.01200 0.00538 -0.0952 0.4265 0.0242
-1.750 0.3349 0.01155 0.00479 -0.0954 0.4158 0.0244
-1.500 0.3636 0.01117 0.00429 -0.0956 0.4065 0.0246
-1.250 0.3923 0.01083 0.00386 -0.0957 0.3988 0.0248
-1.000 0.4210 0.01061 0.00356 -0.0959 0.3905 0.0250
-0.750 0.4497 0.01043 0.00331 -0.0960 0.3835 0.0253
-0.500 0.4784 0.01022 0.00303 -0.0962 0.3759 0.0255
-0.250 0.5071 0.01004 0.00279 -0.0964 0.3695 0.0256
0.000 0.5358 0.00991 0.00261 -0.0965 0.3622 0.0258
0.250 0.5645 0.00983 0.00247 -0.0967 0.3556 0.0260
0.500 0.5931 0.00979 0.00239 -0.0968 0.3482 0.0262
0.750 0.6216 0.00977 0.00234 -0.0970 0.3417 0.0264
1.000 0.6505 0.00962 0.00212 -0.0972 0.3354 0.0279
1.250 0.6790 0.00963 0.00208 -0.0973 0.3275 0.0290
1.500 0.7073 0.00967 0.00207 -0.0975 0.3178 0.0299
1.750 0.7357 0.00972 0.00209 -0.0976 0.3098 0.0306
2.000 0.7640 0.00977 0.00211 -0.0977 0.3037 0.0314
2.250 0.7923 0.00983 0.00215 -0.0978 0.2986 0.0322
2.500 0.8206 0.00987 0.00220 -0.0979 0.2941 0.0334
2.750 0.8488 0.00994 0.00226 -0.0980 0.2889 0.0354
3.000 0.8768 0.01002 0.00234 -0.0981 0.2840 0.0441
3.250 0.9050 0.01007 0.00245 -0.0982 0.2801 0.0659
3.500 0.9330 0.01016 0.00255 -0.0983 0.2747 0.0716
3.750 0.9606 0.01030 0.00267 -0.0984 0.2653 0.0758
4.250 1.0156 0.01061 0.00291 -0.0985 0.2464 0.0829
4.500 1.0428 0.01078 0.00308 -0.0985 0.2358 0.0919
4.750 1.0654 0.00951 0.00345 -0.0980 0.2234 1.0000
5.000 1.0921 0.00979 0.00364 -0.0980 0.2092 1.0000
5.250 1.1157 0.01054 0.00408 -0.0976 0.1558 1.0000
5.500 1.1374 0.01158 0.00481 -0.0970 0.0957 1.0000
5.750 1.1571 0.01292 0.00574 -0.0960 0.0161 1.0000
6.000 1.1830 0.01323 0.00605 -0.0958 0.0128 1.0000
6.250 1.2091 0.01351 0.00635 -0.0957 0.0116 1.0000
6.500 1.2348 0.01382 0.00668 -0.0954 0.0106 1.0000
6.750 1.2602 0.01417 0.00705 -0.0952 0.0096 1.0000
7.000 1.2851 0.01456 0.00748 -0.0949 0.0087 1.0000
7.250 1.3101 0.01490 0.00784 -0.0946 0.0080 1.0000
7.500 1.3348 0.01528 0.00823 -0.0942 0.0074 1.0000
7.750 1.3589 0.01569 0.00866 -0.0938 0.0069 1.0000
8.000 1.3822 0.01618 0.00919 -0.0933 0.0064 1.0000
8.250 1.4049 0.01671 0.00978 -0.0927 0.0061 1.0000
8.500 1.4278 0.01719 0.01029 -0.0921 0.0058 1.0000
8.750 1.4503 0.01768 0.01081 -0.0915 0.0055 1.0000
9.000 1.4723 0.01818 0.01134 -0.0908 0.0051 1.0000
9.250 1.4937 0.01870 0.01189 -0.0901 0.0048 1.0000
9.500 1.5141 0.01929 0.01253 -0.0892 0.0046 1.0000
9.750 1.5321 0.02005 0.01335 -0.0880 0.0044 1.0000
10.000 1.5488 0.02087 0.01424 -0.0866 0.0042 1.0000
10.250 1.5656 0.02160 0.01504 -0.0852 0.0041 1.0000
10.500 1.5804 0.02241 0.01592 -0.0835 0.0040 1.0000
10.750 1.5927 0.02329 0.01688 -0.0815 0.0038 1.0000
11.000 1.6002 0.02425 0.01791 -0.0787 0.0037 1.0000
11.250 1.6060 0.02533 0.01909 -0.0759 0.0036 1.0000
11.500 1.6111 0.02659 0.02044 -0.0734 0.0035 1.0000
11.750 1.6154 0.02806 0.02200 -0.0712 0.0034 1.0000
12.000 1.6196 0.02970 0.02372 -0.0694 0.0033 1.0000
12.250 1.6234 0.03155 0.02565 -0.0680 0.0033 1.0000
12.500 1.6270 0.03361 0.02780 -0.0670 0.0032 1.0000
12.750 1.6299 0.03590 0.03017 -0.0664 0.0031 1.0000
13.000 1.6299 0.03870 0.03307 -0.0660 0.0031 1.0000
13.250 1.6282 0.04188 0.03634 -0.0659 0.0030 1.0000
13.500 1.6242 0.04552 0.04009 -0.0662 0.0029 1.0000
13.750 1.6160 0.04990 0.04460 -0.0668 0.0029 1.0000
14.000 1.6029 0.05509 0.04993 -0.0677 0.0028 1.0000
14.250 1.5870 0.06076 0.05574 -0.0688 0.0028 1.0000
14.500 1.5717 0.06641 0.06151 -0.0700 0.0028 1.0000
14.750 1.5587 0.07176 0.06698 -0.0711 0.0028 1.0000
15.000 1.5459 0.07721 0.07254 -0.0723 0.0027 1.0000
15.250 1.5325 0.08277 0.07821 -0.0736 0.0027 1.0000
15.500 1.5193 0.08839 0.08393 -0.0750 0.0027 1.0000
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Polar data table (+)
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