GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.49 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe182-il-1000000.txt Download as CSV file: xf-goe182-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 182 (MVA H.27) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3383 0.09428 0.09273 -0.0189 1.0000 0.0198
-8.500 -0.3341 0.09040 0.08886 -0.0209 1.0000 0.0198
-8.250 -0.3352 0.08588 0.08436 -0.0226 1.0000 0.0201
-8.000 -0.3255 0.08410 0.08260 -0.0227 1.0000 0.0203
-7.750 -0.3121 0.08200 0.08051 -0.0242 0.9955 0.0206
-7.500 -0.2890 0.07895 0.07746 -0.0290 0.9794 0.0212
-7.250 -0.2709 0.07563 0.07411 -0.0334 0.9595 0.0222
-7.000 -0.2495 0.01926 0.01619 -0.1006 0.9567 0.0248
-6.750 -0.2254 0.01878 0.01563 -0.0998 0.9367 0.0252
-6.500 -0.2019 0.01826 0.01498 -0.0989 0.9055 0.0256
-6.250 -0.1792 0.01778 0.01422 -0.0978 0.8458 0.0261
-6.000 -0.1549 0.01710 0.01316 -0.0973 0.7887 0.0268
-5.750 -0.1291 0.01581 0.01149 -0.0973 0.7590 0.0276
-5.500 -0.1023 0.01480 0.01017 -0.0972 0.7394 0.0282
-5.250 -0.0749 0.01418 0.00933 -0.0971 0.7242 0.0286
-5.000 -0.0473 0.01355 0.00847 -0.0970 0.7108 0.0290
-4.750 -0.0207 0.01197 0.00663 -0.0971 0.6987 0.0299
-4.500 0.0070 0.01151 0.00605 -0.0970 0.6860 0.0304
-4.250 0.0350 0.01114 0.00558 -0.0969 0.6727 0.0309
-4.000 0.0630 0.01079 0.00513 -0.0967 0.6584 0.0315
-3.750 0.0910 0.01047 0.00470 -0.0965 0.6418 0.0321
-3.500 0.1190 0.01018 0.00429 -0.0964 0.6225 0.0328
-3.250 0.1469 0.01001 0.00399 -0.0962 0.5994 0.0336
-3.000 0.1748 0.00984 0.00368 -0.0960 0.5761 0.0341
-2.750 0.2027 0.00968 0.00340 -0.0958 0.5552 0.0345
-2.500 0.2306 0.00937 0.00296 -0.0956 0.5364 0.0350
-2.250 0.2585 0.00904 0.00253 -0.0955 0.5195 0.0362
-2.000 0.2866 0.00892 0.00234 -0.0953 0.5038 0.0373
-1.750 0.3148 0.00886 0.00220 -0.0952 0.4884 0.0385
-1.500 0.3429 0.00881 0.00208 -0.0951 0.4725 0.0399
-1.250 0.3710 0.00881 0.00200 -0.0949 0.4555 0.0412
-1.000 0.3991 0.00872 0.00181 -0.0948 0.4370 0.0432
-0.750 0.4271 0.00871 0.00173 -0.0946 0.4169 0.0462
-0.500 0.4550 0.00877 0.00170 -0.0945 0.3950 0.0494
-0.250 0.4828 0.00880 0.00165 -0.0943 0.3734 0.0564
0.000 0.5106 0.00886 0.00164 -0.0941 0.3546 0.0647
0.250 0.5384 0.00895 0.00166 -0.0940 0.3386 0.0718
0.750 0.5941 0.00897 0.00167 -0.0938 0.3136 0.1060
1.000 0.6219 0.00898 0.00175 -0.0937 0.3038 0.1557
1.250 0.6496 0.00905 0.00181 -0.0936 0.2942 0.1777
1.500 0.6776 0.00905 0.00188 -0.0935 0.2872 0.2107
1.750 0.7051 0.00906 0.00199 -0.0934 0.2791 0.2777
2.000 0.7327 0.00889 0.00213 -0.0934 0.2736 0.4094
2.250 0.7599 0.00881 0.00226 -0.0933 0.2676 0.5236
2.500 0.7868 0.00796 0.00240 -0.0931 0.2622 1.0000
2.750 0.8147 0.00807 0.00247 -0.0929 0.2589 1.0000
3.000 0.8424 0.00821 0.00256 -0.0928 0.2552 1.0000
3.250 0.8698 0.00837 0.00267 -0.0926 0.2511 1.0000
3.500 0.8973 0.00854 0.00280 -0.0924 0.2476 1.0000
3.750 0.9250 0.00865 0.00291 -0.0923 0.2460 1.0000
4.000 0.9526 0.00878 0.00302 -0.0921 0.2442 1.0000
4.250 0.9801 0.00891 0.00315 -0.0920 0.2423 1.0000
4.500 1.0075 0.00906 0.00328 -0.0918 0.2405 1.0000
4.750 1.0348 0.00922 0.00343 -0.0916 0.2386 1.0000
5.000 1.0618 0.00941 0.00360 -0.0914 0.2363 1.0000
5.250 1.0884 0.00964 0.00381 -0.0912 0.2331 1.0000
5.500 1.1158 0.00976 0.00394 -0.0910 0.2321 1.0000
5.750 1.1431 0.00988 0.00408 -0.0909 0.2307 1.0000
6.000 1.1703 0.01002 0.00424 -0.0907 0.2293 1.0000
6.250 1.1973 0.01016 0.00439 -0.0905 0.2272 1.0000
6.500 1.2242 0.01032 0.00455 -0.0904 0.2245 1.0000
6.750 1.2505 0.01055 0.00476 -0.0901 0.2206 1.0000
7.000 1.2771 0.01072 0.00494 -0.0899 0.2176 1.0000
7.250 1.3043 0.01081 0.00507 -0.0898 0.2148 1.0000
7.500 1.3310 0.01096 0.00524 -0.0896 0.2113 1.0000
7.750 1.3571 0.01118 0.00545 -0.0893 0.2070 1.0000
8.000 1.3833 0.01137 0.00566 -0.0891 0.2030 1.0000
8.250 1.4099 0.01151 0.00581 -0.0889 0.1971 1.0000
8.500 1.4355 0.01177 0.00605 -0.0886 0.1884 1.0000
8.750 1.4595 0.01219 0.00633 -0.0882 0.1629 1.0000
9.000 1.4725 0.01393 0.00765 -0.0864 0.0963 1.0000
9.250 1.4874 0.01540 0.00881 -0.0848 0.0512 1.0000
9.500 1.5084 0.01609 0.00950 -0.0839 0.0415 1.0000
9.750 1.5295 0.01674 0.01012 -0.0831 0.0339 1.0000
10.000 1.5497 0.01743 0.01078 -0.0821 0.0267 1.0000
10.250 1.5698 0.01811 0.01145 -0.0812 0.0221 1.0000
10.500 1.5895 0.01877 0.01215 -0.0801 0.0194 1.0000
10.750 1.6083 0.01947 0.01286 -0.0790 0.0175 1.0000
11.000 1.6257 0.02026 0.01370 -0.0777 0.0160 1.0000
11.250 1.6439 0.02091 0.01440 -0.0765 0.0151 1.0000
11.500 1.6600 0.02167 0.01522 -0.0751 0.0143 1.0000
11.750 1.6724 0.02266 0.01626 -0.0732 0.0134 1.0000
12.000 1.6790 0.02377 0.01746 -0.0704 0.0128 1.0000
12.250 1.6889 0.02465 0.01841 -0.0682 0.0125 1.0000
12.500 1.6965 0.02572 0.01956 -0.0660 0.0121 1.0000
12.750 1.7026 0.02699 0.02091 -0.0639 0.0118 1.0000
13.000 1.7070 0.02848 0.02249 -0.0620 0.0114 1.0000
13.250 1.7097 0.03029 0.02439 -0.0605 0.0111 1.0000
13.500 1.7094 0.03261 0.02680 -0.0593 0.0108 1.0000
13.750 1.7041 0.03580 0.03011 -0.0588 0.0105 1.0000
14.000 1.6928 0.04015 0.03460 -0.0592 0.0103 1.0000
14.250 1.6775 0.04533 0.03994 -0.0601 0.0101 1.0000
14.500 1.6721 0.04934 0.04407 -0.0609 0.0100 1.0000
14.750 1.6626 0.05405 0.04891 -0.0620 0.0099 1.0000
15.000 1.6491 0.05945 0.05444 -0.0634 0.0098 1.0000
15.250 1.6313 0.06551 0.06063 -0.0650 0.0098 1.0000
15.500 1.6118 0.07187 0.06713 -0.0667 0.0097 1.0000
15.750 1.5909 0.07848 0.07386 -0.0685 0.0097 1.0000
16.000 1.5700 0.08528 0.08079 -0.0704 0.0097 1.0000
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Polar data table (+)
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