GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il) Reynolds number: 200,000 Max Cl/Cd: 74.17 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe142-il-200000.txt Download as CSV file: xf-goe142-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 142 (MVA H.19) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.3613 0.08730 0.08400 -0.0279 1.0000 0.0311
-6.750 -0.3567 0.08313 0.07986 -0.0247 1.0000 0.0318
-6.500 -0.3487 0.07989 0.07665 -0.0243 1.0000 0.0325
-6.250 -0.3403 0.07688 0.07366 -0.0251 1.0000 0.0333
-6.000 -0.3319 0.07395 0.07074 -0.0263 1.0000 0.0342
-5.750 -0.3231 0.07103 0.06784 -0.0277 1.0000 0.0352
-5.500 -0.3139 0.06813 0.06495 -0.0292 1.0000 0.0364
-5.250 -0.3033 0.06520 0.06201 -0.0308 1.0000 0.0379
-5.000 -0.2859 0.06224 0.05899 -0.0342 1.0000 0.0401
-4.750 -0.2526 0.05995 0.05645 -0.0407 1.0000 0.0417
-4.500 -0.2347 0.05713 0.05349 -0.0419 1.0000 0.0418
-4.250 -0.2322 0.05116 0.04762 -0.0417 1.0000 0.0431
-4.000 -0.2231 0.04867 0.04515 -0.0406 1.0000 0.0443
-3.750 -0.1849 0.04544 0.04184 -0.0453 0.9962 0.0494
-3.500 -0.1235 0.04039 0.03623 -0.0543 0.9919 0.0556
-3.250 -0.0896 0.03670 0.03255 -0.0580 0.9874 0.0580
-3.000 -0.0447 0.03371 0.02936 -0.0627 0.9838 0.0639
-2.250 0.1262 0.00636 0.00058 -0.0771 0.9561 0.0533
-1.750 0.1804 0.01686 0.00999 -0.0786 0.9597 0.0558
-1.500 0.2239 0.01526 0.00824 -0.0816 0.9553 0.0604
-1.250 0.2608 0.01459 0.00734 -0.0828 0.9458 0.0679
-1.000 0.2962 0.01334 0.00609 -0.0840 0.9366 0.0756
-0.750 0.3307 0.01258 0.00530 -0.0848 0.9268 0.0866
-0.500 0.3609 0.01201 0.00471 -0.0846 0.9138 0.0981
-0.250 0.3882 0.01147 0.00423 -0.0840 0.8986 0.1142
0.000 0.4143 0.01103 0.00386 -0.0831 0.8813 0.1356
0.250 0.4402 0.01056 0.00352 -0.0822 0.8631 0.1770
0.500 0.4635 0.00838 0.00327 -0.0806 0.8456 1.0000
0.750 0.4891 0.00840 0.00308 -0.0795 0.8246 1.0000
1.000 0.5148 0.00846 0.00295 -0.0785 0.8026 1.0000
1.250 0.5405 0.00854 0.00286 -0.0776 0.7787 1.0000
1.500 0.5663 0.00865 0.00280 -0.0768 0.7544 1.0000
1.750 0.5920 0.00879 0.00277 -0.0759 0.7289 1.0000
2.000 0.6178 0.00896 0.00277 -0.0752 0.7021 1.0000
2.250 0.6436 0.00915 0.00281 -0.0745 0.6744 1.0000
2.500 0.6694 0.00937 0.00287 -0.0738 0.6465 1.0000
2.750 0.6951 0.00961 0.00297 -0.0732 0.6182 1.0000
3.000 0.7208 0.00988 0.00308 -0.0726 0.5902 1.0000
3.250 0.7465 0.01016 0.00322 -0.0721 0.5625 1.0000
3.500 0.7721 0.01045 0.00338 -0.0716 0.5356 1.0000
3.750 0.7977 0.01077 0.00360 -0.0711 0.5098 1.0000
4.000 0.8233 0.01110 0.00382 -0.0706 0.4852 1.0000
4.250 0.8487 0.01145 0.00406 -0.0701 0.4614 1.0000
4.500 0.8743 0.01179 0.00433 -0.0697 0.4386 1.0000
4.750 0.8995 0.01218 0.00464 -0.0693 0.4176 1.0000
5.000 0.9251 0.01254 0.00497 -0.0689 0.3964 1.0000
5.250 0.9503 0.01294 0.00531 -0.0684 0.3774 1.0000
5.500 0.9754 0.01336 0.00568 -0.0680 0.3592 1.0000
5.750 1.0006 0.01376 0.00610 -0.0676 0.3413 1.0000
6.000 1.0256 0.01419 0.00653 -0.0671 0.3246 1.0000
6.250 1.0504 0.01464 0.00697 -0.0667 0.3085 1.0000
6.500 1.0749 0.01509 0.00741 -0.0662 0.2924 1.0000
6.750 1.0990 0.01548 0.00781 -0.0657 0.2734 1.0000
7.000 1.1231 0.01583 0.00822 -0.0652 0.2529 1.0000
7.250 1.1467 0.01628 0.00867 -0.0646 0.2354 1.0000
7.500 1.1706 0.01669 0.00915 -0.0641 0.2170 1.0000
7.750 1.1941 0.01713 0.00963 -0.0636 0.1963 1.0000
8.000 1.2172 0.01761 0.01016 -0.0630 0.1707 1.0000
8.250 1.2380 0.01842 0.01084 -0.0622 0.1271 1.0000
8.500 1.2492 0.02075 0.01260 -0.0603 0.0589 1.0000
8.750 1.2638 0.02246 0.01431 -0.0585 0.0449 1.0000
9.000 1.2764 0.02427 0.01621 -0.0565 0.0390 1.0000
9.250 1.2915 0.02568 0.01772 -0.0548 0.0345 1.0000
9.500 1.2978 0.02820 0.02026 -0.0522 0.0309 1.0000
9.750 1.3130 0.02965 0.02188 -0.0505 0.0293 1.0000
10.000 1.3263 0.03144 0.02387 -0.0486 0.0277 1.0000
10.250 1.3391 0.03342 0.02599 -0.0467 0.0263 1.0000
10.500 1.3513 0.03552 0.02824 -0.0449 0.0251 1.0000
10.750 1.3616 0.03772 0.03054 -0.0431 0.0238 1.0000
11.000 1.3688 0.04194 0.03496 -0.0414 0.0224 1.0000
11.250 1.3712 0.04510 0.03844 -0.0389 0.0218 1.0000
11.500 1.3707 0.04761 0.04123 -0.0361 0.0216 1.0000
11.750 1.3666 0.05045 0.04436 -0.0334 0.0214 1.0000
12.000 1.3590 0.05364 0.04783 -0.0310 0.0213 1.0000
12.250 1.3485 0.05723 0.05169 -0.0293 0.0212 1.0000
12.500 1.3355 0.06124 0.05598 -0.0283 0.0212 1.0000
12.750 1.3204 0.06575 0.06074 -0.0281 0.0213 1.0000
13.000 1.3036 0.07080 0.06603 -0.0289 0.0213 1.0000
13.250 1.2855 0.07646 0.07191 -0.0307 0.0214 1.0000
13.500 1.2662 0.08273 0.07839 -0.0334 0.0215 1.0000
13.750 1.2458 0.08967 0.08552 -0.0369 0.0216 1.0000
14.000 1.2245 0.09726 0.09328 -0.0410 0.0218 1.0000
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Polar data table (+)
Polar graphs
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