GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Reynolds number: 500,000 Max Cl/Cd: 80.62 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe344-il-500000.txt Download as CSV file: xf-goe344-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 344 (PFALZ 71) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5213 0.08489 0.08257 -0.0141 1.0000 0.0293
-8.000 -0.5219 0.08161 0.07931 -0.0155 1.0000 0.0300
-7.750 -0.5205 0.07783 0.07553 -0.0177 1.0000 0.0310
-7.500 -0.5172 0.07037 0.06800 -0.0256 1.0000 0.0338
-7.250 -0.5769 0.03383 0.03039 -0.0367 1.0000 0.0271
-7.000 -0.5787 0.02494 0.02058 -0.0354 1.0000 0.0280
-6.750 -0.5593 0.02375 0.01929 -0.0343 1.0000 0.0289
-6.500 -0.5381 0.02316 0.01868 -0.0332 1.0000 0.0298
-6.250 -0.5173 0.02227 0.01766 -0.0321 1.0000 0.0311
-6.000 -0.4972 0.02071 0.01581 -0.0309 1.0000 0.0323
-5.750 -0.4761 0.01937 0.01418 -0.0296 1.0000 0.0332
-5.500 -0.4539 0.01870 0.01330 -0.0284 1.0000 0.0338
-5.250 -0.4328 0.01622 0.01048 -0.0275 1.0000 0.0353
-5.000 -0.4098 0.01548 0.00967 -0.0266 1.0000 0.0365
-4.750 -0.3863 0.01484 0.00894 -0.0258 1.0000 0.0374
-4.500 -0.3623 0.01426 0.00826 -0.0249 1.0000 0.0384
-4.250 -0.3380 0.01380 0.00773 -0.0242 1.0000 0.0397
-4.000 -0.3129 0.01334 0.00719 -0.0236 1.0000 0.0407
-3.750 -0.2872 0.01290 0.00665 -0.0230 1.0000 0.0415
-3.500 -0.2582 0.01253 0.00622 -0.0232 0.9995 0.0422
-3.250 -0.2197 0.01160 0.00523 -0.0255 0.9975 0.0442
-3.000 -0.1795 0.01118 0.00481 -0.0281 0.9951 0.0467
-2.750 -0.1411 0.01081 0.00444 -0.0302 0.9923 0.0488
-2.500 -0.1027 0.01046 0.00407 -0.0324 0.9886 0.0513
-2.250 -0.0623 0.01001 0.00365 -0.0350 0.9856 0.0565
-2.000 -0.0229 0.00964 0.00334 -0.0373 0.9818 0.0671
-1.750 0.0132 0.00926 0.00311 -0.0390 0.9766 0.0948
-1.500 0.0525 0.00905 0.00298 -0.0414 0.9731 0.1162
-1.250 0.0868 0.00886 0.00284 -0.0426 0.9668 0.1302
-1.000 0.1241 0.00863 0.00266 -0.0445 0.9610 0.1431
-0.750 0.1575 0.00839 0.00247 -0.0455 0.9520 0.1551
-0.500 0.1928 0.00814 0.00229 -0.0469 0.9421 0.1693
-0.250 0.2287 0.00788 0.00209 -0.0484 0.9279 0.1866
0.000 0.2635 0.00763 0.00194 -0.0496 0.9071 0.2138
0.250 0.2937 0.00740 0.00187 -0.0499 0.8788 0.2814
0.500 0.3196 0.00714 0.00182 -0.0493 0.8325 0.3875
0.750 0.3358 0.00589 0.00190 -0.0458 0.7606 0.9633
1.000 0.3868 0.00639 0.00205 -0.0506 0.6967 0.9916
1.250 0.4374 0.00679 0.00217 -0.0556 0.6424 1.0000
1.500 0.4617 0.00700 0.00218 -0.0547 0.5987 1.0000
1.750 0.4859 0.00723 0.00221 -0.0539 0.5569 1.0000
2.000 0.5099 0.00747 0.00226 -0.0530 0.5160 1.0000
2.250 0.5339 0.00771 0.00231 -0.0521 0.4748 1.0000
2.500 0.5577 0.00798 0.00238 -0.0512 0.4293 1.0000
2.750 0.5814 0.00826 0.00247 -0.0503 0.3874 1.0000
3.000 0.6051 0.00855 0.00259 -0.0495 0.3556 1.0000
3.250 0.6289 0.00882 0.00272 -0.0486 0.3297 1.0000
3.500 0.6531 0.00905 0.00285 -0.0478 0.3105 1.0000
3.750 0.6775 0.00924 0.00299 -0.0471 0.2970 1.0000
4.000 0.7020 0.00943 0.00313 -0.0463 0.2841 1.0000
4.250 0.7265 0.00962 0.00329 -0.0456 0.2723 1.0000
4.500 0.7510 0.00982 0.00345 -0.0449 0.2600 1.0000
4.750 0.7758 0.00998 0.00360 -0.0442 0.2478 1.0000
5.000 0.8005 0.01017 0.00377 -0.0435 0.2361 1.0000
5.250 0.8253 0.01037 0.00395 -0.0428 0.2238 1.0000
5.500 0.8500 0.01059 0.00415 -0.0422 0.2092 1.0000
5.750 0.8747 0.01085 0.00435 -0.0415 0.1913 1.0000
6.000 0.8990 0.01117 0.00458 -0.0409 0.1695 1.0000
6.250 0.9226 0.01161 0.00488 -0.0401 0.1365 1.0000
6.500 0.9447 0.01229 0.00534 -0.0392 0.0995 1.0000
6.750 0.9677 0.01287 0.00581 -0.0384 0.0810 1.0000
7.000 0.9913 0.01335 0.00628 -0.0377 0.0713 1.0000
7.250 1.0143 0.01393 0.00683 -0.0368 0.0637 1.0000
7.500 1.0386 0.01431 0.00726 -0.0362 0.0590 1.0000
7.750 1.0605 0.01503 0.00796 -0.0352 0.0530 1.0000
8.000 1.0853 0.01532 0.00832 -0.0347 0.0499 1.0000
8.250 1.1086 0.01581 0.00883 -0.0340 0.0456 1.0000
8.500 1.1306 0.01645 0.00953 -0.0331 0.0416 1.0000
8.750 1.1545 0.01685 0.00996 -0.0324 0.0377 1.0000
9.000 1.1751 0.01763 0.01076 -0.0313 0.0336 1.0000
9.250 1.1985 0.01806 0.01124 -0.0307 0.0304 1.0000
9.500 1.2164 0.01912 0.01232 -0.0292 0.0272 1.0000
9.750 1.2387 0.01963 0.01293 -0.0283 0.0254 1.0000
10.000 1.2599 0.02023 0.01359 -0.0274 0.0235 1.0000
10.250 1.2740 0.02157 0.01497 -0.0254 0.0215 1.0000
10.500 1.2949 0.02215 0.01566 -0.0244 0.0205 1.0000
10.750 1.3133 0.02295 0.01656 -0.0231 0.0194 1.0000
11.000 1.3305 0.02380 0.01748 -0.0216 0.0184 1.0000
11.250 1.3442 0.02493 0.01868 -0.0197 0.0176 1.0000
11.500 1.3500 0.02679 0.02067 -0.0168 0.0168 1.0000
11.750 1.3633 0.02781 0.02183 -0.0148 0.0164 1.0000
12.000 1.3741 0.02894 0.02309 -0.0126 0.0158 1.0000
12.250 1.3810 0.03009 0.02438 -0.0098 0.0153 1.0000
12.500 1.3867 0.03128 0.02567 -0.0070 0.0148 1.0000
12.750 1.3913 0.03261 0.02710 -0.0044 0.0144 1.0000
13.000 1.3940 0.03415 0.02873 -0.0020 0.0140 1.0000
13.250 1.3927 0.03619 0.03089 0.0004 0.0137 1.0000
13.500 1.3852 0.03904 0.03388 0.0025 0.0134 1.0000
13.750 1.3718 0.04288 0.03791 0.0041 0.0132 1.0000
14.000 1.3671 0.04607 0.04128 0.0044 0.0130 1.0000
14.250 1.3621 0.04965 0.04505 0.0039 0.0129 1.0000
14.500 1.3553 0.05387 0.04945 0.0025 0.0128 1.0000
14.750 1.3458 0.05880 0.05457 0.0003 0.0127 1.0000
15.000 1.3343 0.06437 0.06032 -0.0024 0.0126 1.0000
15.250 1.3207 0.07050 0.06663 -0.0057 0.0125 1.0000
15.500 1.3046 0.07723 0.07354 -0.0093 0.0125 1.0000
15.750 1.2867 0.08442 0.08088 -0.0132 0.0125 1.0000
16.000 1.2669 0.09212 0.08875 -0.0173 0.0125 1.0000
16.250 1.2462 0.10020 0.09698 -0.0217 0.0125 1.0000
16.500 1.2241 0.10875 0.10568 -0.0264 0.0126 1.0000
16.750 1.2009 0.11789 0.11496 -0.0315 0.0126 1.0000
17.000 1.1764 0.12763 0.12484 -0.0369 0.0127 1.0000
17.250 1.1497 0.13841 0.13577 -0.0431 0.0128 1.0000
17.500 1.1170 0.15136 0.14886 -0.0506 0.0130 1.0000
17.750 1.0781 0.16746 0.16512 -0.0599 0.0132 1.0000
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