GOE 121 (MVA H.1) AIRFOIL (goe121-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 121 (MVA H.1) AIRFOIL (goe121-il) Reynolds number: 50,000 Max Cl/Cd: 40.59 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe121-il-50000.txt Download as CSV file: xf-goe121-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 121 (MVA H.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3686 0.11477 0.10755 -0.0160 1.0000 0.1334
-8.500 -0.3715 0.11391 0.10678 -0.0180 1.0000 0.1367
-8.250 -0.3834 0.11480 0.10783 -0.0206 1.0000 0.1378
-8.000 -0.3557 0.10625 0.09921 -0.0180 1.0000 0.1435
-7.750 -0.3534 0.10405 0.09708 -0.0185 1.0000 0.1491
-7.500 -0.3627 0.10427 0.09745 -0.0212 1.0000 0.1522
-7.250 -0.3525 0.09936 0.09259 -0.0199 1.0000 0.1555
-7.000 -0.3438 0.09597 0.08923 -0.0191 1.0000 0.1609
-6.750 -0.3449 0.09490 0.08827 -0.0221 1.0000 0.1664
-6.500 -0.3415 0.09206 0.08550 -0.0236 1.0000 0.1692
-6.250 -0.3322 0.08818 0.08166 -0.0209 1.0000 0.1747
-6.000 -0.3296 0.08735 0.08089 -0.0258 1.0000 0.1821
-5.500 -0.3174 0.08110 0.07476 -0.0240 1.0000 0.1956
-5.250 -0.3121 0.07816 0.07189 -0.0239 1.0000 0.2017
-5.000 -0.3015 0.07696 0.07067 -0.0290 1.0000 0.2135
-4.750 -0.2986 0.07301 0.06683 -0.0238 1.0000 0.2190
-4.250 -0.2732 0.06876 0.06250 -0.0296 1.0000 0.2436
-4.000 -0.2693 0.06536 0.05920 -0.0256 1.0000 0.2511
-3.750 -0.2569 0.06276 0.05660 -0.0263 1.0000 0.2650
-3.500 -0.2366 0.06069 0.05446 -0.0304 1.0000 0.2878
-3.250 -0.2281 0.05767 0.05149 -0.0284 1.0000 0.3048
-3.000 -0.2158 0.05516 0.04901 -0.0279 1.0000 0.3337
-2.750 -0.2066 0.05257 0.04646 -0.0259 1.0000 0.3659
-1.750 -0.1792 0.04265 0.03690 -0.0122 1.0000 0.5584
-1.500 -0.1647 0.04015 0.03445 -0.0103 1.0000 0.5921
-1.250 -0.1330 0.03777 0.03201 -0.0136 1.0000 0.6129
-1.000 0.0899 0.03547 0.02698 -0.0679 1.0000 0.2092
-0.750 0.1280 0.03348 0.02453 -0.0708 1.0000 0.1920
-0.500 0.1642 0.03191 0.02242 -0.0731 1.0000 0.1848
-0.250 0.1914 0.03102 0.02138 -0.0741 1.0000 0.1894
0.000 0.2200 0.03040 0.02046 -0.0753 1.0000 0.1995
0.250 0.2464 0.02990 0.01982 -0.0762 1.0000 0.2102
0.500 0.2724 0.02962 0.01937 -0.0771 1.0000 0.2292
0.750 0.3364 0.02904 0.01868 -0.0844 0.9855 0.2990
1.000 0.3978 0.02841 0.01807 -0.0911 0.9687 0.3541
1.250 0.4561 0.02784 0.01774 -0.0971 0.9497 0.4087
1.500 0.5090 0.02617 0.01734 -0.1013 0.9310 1.0000
1.750 0.5586 0.02664 0.01727 -0.1049 0.9071 1.0000
2.000 0.6152 0.02680 0.01722 -0.1097 0.8865 1.0000
2.250 0.6567 0.02707 0.01741 -0.1117 0.8621 1.0000
2.500 0.7050 0.02695 0.01727 -0.1142 0.8419 1.0000
2.750 0.7382 0.02713 0.01744 -0.1142 0.8174 1.0000
3.000 0.7796 0.02681 0.01710 -0.1148 0.7971 1.0000
3.250 0.8091 0.02687 0.01720 -0.1138 0.7730 1.0000
3.500 0.8453 0.02643 0.01676 -0.1130 0.7526 1.0000
3.750 0.8720 0.02652 0.01686 -0.1114 0.7283 1.0000
4.000 0.9035 0.02622 0.01657 -0.1099 0.7071 1.0000
4.250 0.9274 0.02653 0.01691 -0.1081 0.6830 1.0000
4.500 0.9549 0.02666 0.01705 -0.1067 0.6627 1.0000
4.750 0.9804 0.02710 0.01753 -0.1054 0.6432 1.0000
5.000 1.0040 0.02774 0.01830 -0.1043 0.6237 1.0000
5.250 1.0297 0.02820 0.01884 -0.1031 0.6056 1.0000
5.500 1.0569 0.02848 0.01916 -0.1018 0.5876 1.0000
5.750 1.0804 0.02910 0.01988 -0.1004 0.5674 1.0000
6.000 1.1051 0.02957 0.02044 -0.0988 0.5464 1.0000
6.250 1.1317 0.02998 0.02085 -0.0973 0.5259 1.0000
6.500 1.1525 0.03103 0.02208 -0.0958 0.5043 1.0000
6.750 1.1779 0.03146 0.02251 -0.0941 0.4818 1.0000
7.000 1.1983 0.03156 0.02265 -0.0916 0.4521 1.0000
7.250 1.2178 0.03160 0.02276 -0.0891 0.4230 1.0000
7.500 1.2347 0.03111 0.02224 -0.0860 0.3886 1.0000
7.750 1.2464 0.03071 0.02189 -0.0824 0.3488 1.0000
8.000 1.2494 0.03080 0.02204 -0.0778 0.2921 1.0000
8.250 1.2394 0.03251 0.02310 -0.0723 0.1965 1.0000
8.500 1.2391 0.03586 0.02575 -0.0686 0.1476 1.0000
8.750 1.2510 0.03840 0.02814 -0.0662 0.1265 1.0000
9.000 1.2658 0.04054 0.03026 -0.0641 0.1133 1.0000
9.250 1.2816 0.04268 0.03227 -0.0624 0.1037 1.0000
9.500 1.3054 0.04528 0.03507 -0.0611 0.0971 1.0000
9.750 1.3376 0.04871 0.03837 -0.0611 0.0924 1.0000
10.000 1.3542 0.05216 0.04237 -0.0595 0.0899 1.0000
10.250 1.3653 0.05575 0.04641 -0.0576 0.0872 1.0000
10.500 1.3738 0.05947 0.05048 -0.0558 0.0851 1.0000
10.750 1.3766 0.06357 0.05498 -0.0537 0.0843 1.0000
11.000 1.3691 0.06797 0.05986 -0.0511 0.0847 1.0000
11.250 1.3527 0.07239 0.06471 -0.0484 0.0853 1.0000
11.500 1.3292 0.07680 0.06946 -0.0458 0.0861 1.0000
11.750 1.3022 0.08179 0.07474 -0.0446 0.0869 1.0000
12.000 1.2728 0.08763 0.08083 -0.0452 0.0878 1.0000
12.250 1.2418 0.09453 0.08794 -0.0476 0.0889 1.0000
12.500 1.2116 0.10253 0.09608 -0.0515 0.0902 1.0000
12.750 1.1872 0.11097 0.10460 -0.0560 0.0915 1.0000
13.000 1.1714 0.11894 0.11260 -0.0597 0.0925 1.0000
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Polar data table (+)
Polar graphs
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