GOE 182 (MVA H.27) AIRFOIL (goe182-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 182 (MVA H.27) AIRFOIL (goe182-il) Reynolds number: 200,000 Max Cl/Cd: 69.42 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe182-il-200000-n5.txt Download as CSV file: xf-goe182-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2930 0.09108 0.08772 -0.0227 1.0000 0.0293
-7.750 -0.2913 0.08806 0.08475 -0.0235 1.0000 0.0290
-7.500 -0.2931 0.08538 0.08214 -0.0237 1.0000 0.0288
-7.250 -0.2954 0.08283 0.07965 -0.0239 1.0000 0.0293
-7.000 -0.2861 0.07850 0.07534 -0.0293 0.9955 0.0305
-6.750 -0.2578 0.07203 0.06884 -0.0401 0.9853 0.0309
-6.500 -0.2263 0.06464 0.06138 -0.0522 0.9737 0.0312
-6.250 -0.1998 0.06223 0.05896 -0.0557 0.9623 0.0327
-6.000 -0.1706 0.05954 0.05621 -0.0601 0.9481 0.0343
-5.750 -0.1384 0.05404 0.05061 -0.0685 0.9272 0.0348
-5.500 -0.1037 0.04787 0.04425 -0.0773 0.8999 0.0351
-5.250 -0.0640 0.03993 0.03596 -0.0877 0.8676 0.0369
-5.000 -0.0241 0.02791 0.02298 -0.0985 0.8393 0.0375
-4.750 0.0055 0.02305 0.01713 -0.1010 0.8061 0.0389
-4.500 0.0311 0.02148 0.01517 -0.1011 0.7751 0.0397
-4.250 0.0573 0.02020 0.01349 -0.1009 0.7488 0.0402
-4.000 0.0839 0.01916 0.01207 -0.1008 0.7271 0.0409
-3.750 0.1109 0.01822 0.01081 -0.1006 0.7084 0.0416
-3.500 0.1383 0.01739 0.00968 -0.1004 0.6916 0.0424
-3.250 0.1658 0.01676 0.00880 -0.1002 0.6752 0.0438
-3.000 0.1933 0.01618 0.00797 -0.1000 0.6582 0.0453
-2.750 0.2209 0.01559 0.00714 -0.0997 0.6400 0.0462
-2.500 0.2483 0.01509 0.00643 -0.0994 0.6204 0.0470
-2.250 0.2754 0.01456 0.00576 -0.0990 0.6003 0.0481
-2.000 0.3025 0.01422 0.00532 -0.0987 0.5800 0.0495
-1.750 0.3296 0.01398 0.00496 -0.0984 0.5606 0.0511
-1.500 0.3568 0.01380 0.00465 -0.0981 0.5420 0.0535
-1.250 0.3840 0.01369 0.00438 -0.0977 0.5242 0.0566
-1.000 0.4111 0.01349 0.00411 -0.0975 0.5070 0.0598
-0.750 0.4383 0.01338 0.00391 -0.0972 0.4901 0.0639
-0.500 0.4656 0.01330 0.00371 -0.0969 0.4727 0.0690
-0.250 0.4929 0.01319 0.00353 -0.0967 0.4545 0.0765
0.000 0.5200 0.01312 0.00340 -0.0965 0.4355 0.0881
0.250 0.5469 0.01307 0.00339 -0.0962 0.4160 0.1137
0.500 0.5737 0.01309 0.00342 -0.0960 0.3972 0.1633
0.750 0.6004 0.01311 0.00348 -0.0958 0.3801 0.2082
1.000 0.6270 0.01314 0.00357 -0.0955 0.3651 0.2607
1.250 0.6536 0.01312 0.00367 -0.0953 0.3524 0.3309
1.500 0.6795 0.01301 0.00383 -0.0950 0.3418 0.4620
2.000 0.7343 0.01238 0.00398 -0.0944 0.3240 1.0000
2.500 0.7878 0.01287 0.00424 -0.0938 0.3107 1.0000
2.750 0.8143 0.01313 0.00440 -0.0935 0.3050 1.0000
3.000 0.8408 0.01340 0.00459 -0.0932 0.3004 1.0000
3.250 0.8675 0.01363 0.00478 -0.0929 0.2959 1.0000
3.500 0.8940 0.01389 0.00498 -0.0926 0.2919 1.0000
3.750 0.9201 0.01419 0.00521 -0.0922 0.2884 1.0000
4.000 0.9463 0.01449 0.00546 -0.0919 0.2855 1.0000
4.250 0.9728 0.01474 0.00571 -0.0916 0.2826 1.0000
4.500 0.9991 0.01501 0.00599 -0.0912 0.2799 1.0000
4.750 1.0253 0.01530 0.00627 -0.0909 0.2774 1.0000
5.000 1.0512 0.01561 0.00656 -0.0906 0.2748 1.0000
5.250 1.0768 0.01596 0.00688 -0.0902 0.2722 1.0000
5.500 1.1024 0.01631 0.00721 -0.0898 0.2697 1.0000
5.750 1.1284 0.01659 0.00754 -0.0895 0.2672 1.0000
6.000 1.1543 0.01689 0.00790 -0.0891 0.2650 1.0000
6.250 1.1800 0.01722 0.00828 -0.0888 0.2631 1.0000
6.500 1.2055 0.01756 0.00867 -0.0884 0.2616 1.0000
6.750 1.2309 0.01792 0.00909 -0.0880 0.2601 1.0000
7.000 1.2560 0.01827 0.00947 -0.0876 0.2578 1.0000
7.250 1.2804 0.01869 0.00986 -0.0871 0.2545 1.0000
7.500 1.3053 0.01899 0.01027 -0.0867 0.2515 1.0000
7.750 1.3302 0.01931 0.01072 -0.0863 0.2490 1.0000
8.000 1.3547 0.01964 0.01116 -0.0858 0.2462 1.0000
8.250 1.3789 0.01998 0.01158 -0.0853 0.2431 1.0000
8.500 1.4026 0.02036 0.01201 -0.0847 0.2402 1.0000
8.750 1.4257 0.02073 0.01247 -0.0841 0.2360 1.0000
9.000 1.4488 0.02092 0.01284 -0.0834 0.2288 1.0000
9.250 1.4700 0.02124 0.01317 -0.0826 0.2202 1.0000
9.500 1.4925 0.02150 0.01358 -0.0819 0.2103 1.0000
9.750 1.5141 0.02186 0.01406 -0.0811 0.1999 1.0000
10.000 1.5350 0.02226 0.01453 -0.0802 0.1805 1.0000
10.250 1.5379 0.02419 0.01592 -0.0776 0.1080 1.0000
10.500 1.5390 0.02641 0.01797 -0.0748 0.0647 1.0000
10.750 1.5406 0.02822 0.01974 -0.0719 0.0518 1.0000
11.000 1.5427 0.02980 0.02141 -0.0691 0.0452 1.0000
11.250 1.5454 0.03139 0.02315 -0.0667 0.0399 1.0000
11.500 1.5448 0.03335 0.02522 -0.0645 0.0360 1.0000
11.750 1.5449 0.03543 0.02743 -0.0628 0.0324 1.0000
12.000 1.5401 0.03821 0.03033 -0.0616 0.0299 1.0000
12.250 1.5374 0.04111 0.03338 -0.0610 0.0277 1.0000
12.500 1.5320 0.04462 0.03704 -0.0611 0.0259 1.0000
12.750 1.5231 0.04883 0.04138 -0.0617 0.0247 1.0000
13.000 1.5104 0.05379 0.04649 -0.0628 0.0238 1.0000
13.250 1.4979 0.05898 0.05184 -0.0642 0.0232 1.0000
13.500 1.4833 0.06463 0.05767 -0.0658 0.0226 1.0000
13.750 1.4667 0.07071 0.06392 -0.0676 0.0222 1.0000
14.000 1.4488 0.07701 0.07038 -0.0695 0.0219 1.0000
14.250 1.4310 0.08340 0.07691 -0.0714 0.0216 1.0000
14.500 1.4142 0.08972 0.08337 -0.0733 0.0213 1.0000
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Polar data table (+)
Polar graphs
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