GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il) Reynolds number: 500,000 Max Cl/Cd: 100.14 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe308-il-500000-n5.txt Download as CSV file: xf-goe308-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 308 (MVA H.40) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3257 0.10021 0.09801 -0.0275 1.0000 0.0078
-9.000 -0.3277 0.09707 0.09491 -0.0275 1.0000 0.0079
-8.750 -0.3292 0.09242 0.09029 -0.0294 0.9993 0.0083
-8.500 -0.3133 0.08893 0.08680 -0.0337 0.9966 0.0088
-8.250 -0.3020 0.08471 0.08259 -0.0381 0.9922 0.0089
-8.000 -0.2857 0.08176 0.07963 -0.0420 0.9875 0.0093
-7.750 -0.2766 0.07753 0.07541 -0.0468 0.9788 0.0094
-7.250 -0.2476 0.06793 0.06577 -0.0581 0.9584 0.0102
-6.250 -0.1543 0.03361 0.03056 -0.0917 0.9024 0.0159
-6.000 -0.1239 0.03246 0.02929 -0.0935 0.8874 0.0163
-5.750 -0.0943 0.03231 0.02905 -0.0945 0.8710 0.0170
-5.500 -0.0977 0.01890 0.01445 -0.0924 0.8541 0.0204
-5.250 -0.0738 0.01774 0.01292 -0.0917 0.8401 0.0214
-5.000 -0.0528 0.01618 0.01102 -0.0908 0.8276 0.0224
-4.750 -0.0289 0.01559 0.01030 -0.0901 0.8158 0.0232
-4.500 -0.0046 0.01506 0.00960 -0.0894 0.8038 0.0239
-4.250 0.0199 0.01463 0.00902 -0.0888 0.7909 0.0249
-4.000 0.0442 0.01409 0.00830 -0.0880 0.7781 0.0258
-3.750 0.0686 0.01344 0.00746 -0.0872 0.7652 0.0265
-3.500 0.0931 0.01285 0.00666 -0.0864 0.7516 0.0271
-3.250 0.1179 0.01246 0.00611 -0.0857 0.7357 0.0280
-3.000 0.1423 0.01212 0.00559 -0.0848 0.7168 0.0287
-2.750 0.1667 0.01177 0.00506 -0.0840 0.6969 0.0291
-2.500 0.1911 0.01151 0.00463 -0.0831 0.6762 0.0294
-2.000 0.2394 0.01110 0.00392 -0.0813 0.6349 0.0298
-1.750 0.2634 0.01087 0.00355 -0.0804 0.6149 0.0300
-1.500 0.2872 0.01060 0.00315 -0.0795 0.5965 0.0304
-1.250 0.3110 0.01037 0.00281 -0.0786 0.5781 0.0310
-1.000 0.3350 0.01020 0.00254 -0.0777 0.5596 0.0319
-0.750 0.3590 0.01013 0.00236 -0.0768 0.5393 0.0324
-0.500 0.3831 0.01009 0.00222 -0.0760 0.5208 0.0326
-0.250 0.4074 0.01007 0.00211 -0.0752 0.5040 0.0331
0.000 0.4318 0.01006 0.00200 -0.0744 0.4883 0.0340
0.250 0.4563 0.01008 0.00194 -0.0736 0.4744 0.0350
0.500 0.4809 0.01009 0.00188 -0.0729 0.4624 0.0366
0.750 0.5059 0.01010 0.00184 -0.0723 0.4532 0.0387
1.250 0.5552 0.01009 0.00189 -0.0710 0.4368 0.0755
1.500 0.5801 0.01017 0.00195 -0.0703 0.4285 0.0912
1.750 0.6052 0.01025 0.00201 -0.0698 0.4199 0.0990
2.000 0.6302 0.01033 0.00207 -0.0692 0.4126 0.1047
2.250 0.6552 0.01038 0.00214 -0.0687 0.4056 0.1108
2.500 0.6800 0.01047 0.00220 -0.0681 0.3994 0.1155
2.750 0.7054 0.01051 0.00227 -0.0676 0.3934 0.1200
3.000 0.7300 0.01058 0.00235 -0.0669 0.3869 0.1283
3.500 0.7785 0.01059 0.00259 -0.0656 0.3737 0.2228
3.750 0.7846 0.00954 0.00270 -0.0614 0.3696 0.7466
4.250 0.8983 0.00968 0.00331 -0.0743 0.3558 0.9813
4.500 0.9354 0.00984 0.00349 -0.0765 0.3502 0.9890
4.750 0.9687 0.01000 0.00365 -0.0779 0.3436 0.9933
5.000 1.0030 0.01018 0.00383 -0.0795 0.3355 0.9968
5.250 1.0380 0.01039 0.00400 -0.0814 0.3205 0.9995
5.500 1.0615 0.01060 0.00417 -0.0807 0.3067 1.0000
5.750 1.0811 0.01083 0.00435 -0.0791 0.2907 1.0000
6.000 1.0989 0.01118 0.00459 -0.0773 0.2665 1.0000
6.250 1.1147 0.01164 0.00489 -0.0751 0.2329 1.0000
6.750 1.1434 0.01282 0.00571 -0.0703 0.1702 1.0000
7.000 1.1579 0.01340 0.00617 -0.0680 0.1448 1.0000
7.250 1.1579 0.01491 0.00715 -0.0633 0.0607 1.0000
7.500 1.1646 0.01597 0.00803 -0.0596 0.0204 1.0000
7.750 1.1809 0.01640 0.00850 -0.0576 0.0163 1.0000
8.000 1.1970 0.01683 0.00899 -0.0555 0.0144 1.0000
8.250 1.2115 0.01735 0.00955 -0.0532 0.0126 1.0000
8.500 1.2230 0.01795 0.01024 -0.0503 0.0111 1.0000
8.750 1.2354 0.01841 0.01078 -0.0477 0.0106 1.0000
9.000 1.2464 0.01896 0.01140 -0.0448 0.0101 1.0000
9.250 1.2573 0.01955 0.01206 -0.0420 0.0094 1.0000
9.500 1.2678 0.02020 0.01278 -0.0393 0.0089 1.0000
9.750 1.2784 0.02087 0.01348 -0.0368 0.0082 1.0000
10.000 1.2829 0.02193 0.01464 -0.0335 0.0077 1.0000
10.250 1.2893 0.02291 0.01571 -0.0307 0.0075 1.0000
10.500 1.2993 0.02373 0.01663 -0.0285 0.0070 1.0000
10.750 1.3043 0.02490 0.01790 -0.0259 0.0069 1.0000
11.000 1.3097 0.02612 0.01921 -0.0236 0.0066 1.0000
11.250 1.3150 0.02741 0.02059 -0.0215 0.0063 1.0000
11.500 1.3176 0.02901 0.02228 -0.0195 0.0061 1.0000
11.750 1.3195 0.03078 0.02415 -0.0177 0.0059 1.0000
12.000 1.3207 0.03272 0.02619 -0.0162 0.0058 1.0000
12.250 1.3218 0.03482 0.02837 -0.0149 0.0056 1.0000
12.500 1.3203 0.03728 0.03094 -0.0139 0.0055 1.0000
12.750 1.3187 0.03994 0.03369 -0.0132 0.0054 1.0000
13.000 1.3102 0.04348 0.03733 -0.0128 0.0052 1.0000
13.250 1.3039 0.04698 0.04096 -0.0127 0.0052 1.0000
13.500 1.3021 0.05009 0.04421 -0.0127 0.0050 1.0000
13.750 1.2952 0.05386 0.04809 -0.0129 0.0050 1.0000
14.000 1.2911 0.05741 0.05176 -0.0132 0.0049 1.0000
14.250 1.2902 0.06068 0.05513 -0.0138 0.0048 1.0000
14.500 1.2884 0.06411 0.05867 -0.0144 0.0045 1.0000
14.750 1.2834 0.06796 0.06263 -0.0150 0.0045 1.0000
15.000 1.2773 0.07198 0.06675 -0.0156 0.0045 1.0000
15.250 1.2730 0.07587 0.07075 -0.0164 0.0043 1.0000
15.500 1.2687 0.07972 0.07470 -0.0172 0.0043 1.0000
15.750 1.2645 0.08369 0.07877 -0.0181 0.0041 1.0000
16.000 1.2605 0.08762 0.08280 -0.0190 0.0041 1.0000
16.250 1.2566 0.09161 0.08689 -0.0200 0.0040 1.0000
16.500 1.2527 0.09564 0.09102 -0.0211 0.0040 1.0000
16.750 1.2479 0.09969 0.09518 -0.0220 0.0040 1.0000
17.000 1.2445 0.10389 0.09947 -0.0235 0.0039 1.0000
17.250 1.2397 0.10821 0.10390 -0.0248 0.0039 1.0000
17.500 1.2361 0.11263 0.10839 -0.0267 0.0037 1.0000
17.750 1.2312 0.11702 0.11289 -0.0282 0.0037 1.0000
18.000 1.2266 0.12160 0.11759 -0.0301 0.0037 1.0000
18.250 1.2219 0.12626 0.12234 -0.0321 0.0036 1.0000
18.500 1.2151 0.13121 0.12744 -0.0340 0.0037 1.0000
18.750 1.2114 0.13591 0.13220 -0.0364 0.0036 1.0000
19.000 1.2047 0.14114 0.13756 -0.0388 0.0036 1.0000
19.250 1.1984 0.14644 0.14297 -0.0416 0.0035 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 308 (MVA H.40) AIRFOIL (goe308-il)