GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Reynolds number: 200,000 Max Cl/Cd: 60.27 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe344-il-200000.txt Download as CSV file: xf-goe344-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3950 0.10012 0.09652 -0.0149 1.0000 0.0549
-9.250 -0.3914 0.09686 0.09327 -0.0150 1.0000 0.0563
-9.000 -0.5150 0.10164 0.09791 -0.0133 1.0000 0.0530
-8.750 -0.4995 0.09879 0.09505 -0.0104 1.0000 0.0545
-8.500 -0.4943 0.09583 0.09211 -0.0105 1.0000 0.0559
-8.250 -0.4927 0.09277 0.08908 -0.0112 1.0000 0.0574
-8.000 -0.4955 0.08967 0.08603 -0.0123 1.0000 0.0591
-7.750 -0.4999 0.08610 0.08249 -0.0159 1.0000 0.0615
-7.500 -0.5011 0.08112 0.07739 -0.0279 1.0000 0.0633
-7.250 -0.5006 0.07533 0.07165 -0.0270 1.0000 0.0642
-7.000 -0.4925 0.07283 0.06919 -0.0238 1.0000 0.0653
-6.750 -0.4826 0.07077 0.06715 -0.0218 1.0000 0.0673
-6.500 -0.4725 0.06783 0.06417 -0.0222 1.0000 0.0703
-6.250 -0.4576 0.06037 0.05629 -0.0316 1.0000 0.0765
-6.000 -0.4485 0.05722 0.05323 -0.0295 1.0000 0.0775
-5.750 -0.4365 0.05499 0.05102 -0.0278 1.0000 0.0789
-5.500 -0.4225 0.05264 0.04865 -0.0269 1.0000 0.0813
-5.250 -0.4023 0.04705 0.04257 -0.0302 1.0000 0.0906
-5.000 -0.3893 0.03267 0.02711 -0.0308 1.0000 0.0643
-4.750 -0.3699 0.02958 0.02381 -0.0297 1.0000 0.0620
-4.500 -0.3498 0.02617 0.01990 -0.0286 1.0000 0.0623
-4.250 -0.3281 0.02335 0.01663 -0.0276 1.0000 0.0622
-4.000 -0.3050 0.02128 0.01413 -0.0266 1.0000 0.0626
-3.750 -0.2810 0.01999 0.01251 -0.0257 1.0000 0.0635
-3.500 -0.2566 0.01815 0.01052 -0.0252 1.0000 0.0660
-3.250 -0.2318 0.01730 0.00957 -0.0245 1.0000 0.0678
-3.000 -0.2065 0.01653 0.00867 -0.0239 1.0000 0.0699
-2.750 -0.1809 0.01585 0.00788 -0.0232 1.0000 0.0726
-2.500 -0.1550 0.01538 0.00729 -0.0227 1.0000 0.0757
-2.250 -0.1286 0.01469 0.00667 -0.0224 1.0000 0.0814
-2.000 -0.1026 0.01433 0.00628 -0.0219 1.0000 0.0882
-1.750 -0.0766 0.01391 0.00595 -0.0215 1.0000 0.0992
-1.500 -0.0510 0.01369 0.00579 -0.0211 1.0000 0.1186
-1.250 -0.0263 0.01362 0.00581 -0.0206 1.0000 0.1393
-1.000 -0.0016 0.01353 0.00578 -0.0202 1.0000 0.1574
-0.750 0.0360 0.01333 0.00563 -0.0224 0.9965 0.1772
-0.500 0.0818 0.01298 0.00548 -0.0264 0.9896 0.2054
-0.250 0.1285 0.01263 0.00532 -0.0305 0.9822 0.2386
0.000 0.1729 0.01212 0.00508 -0.0339 0.9730 0.2826
0.250 0.2303 0.01020 0.00526 -0.0395 0.9726 1.0000
0.500 0.2779 0.00999 0.00493 -0.0434 0.9604 1.0000
0.750 0.3251 0.00972 0.00460 -0.0470 0.9466 1.0000
1.000 0.3700 0.00942 0.00426 -0.0501 0.9280 1.0000
1.250 0.4153 0.00913 0.00393 -0.0532 0.9033 1.0000
1.500 0.4554 0.00892 0.00364 -0.0551 0.8635 1.0000
1.750 0.4881 0.00885 0.00339 -0.0553 0.7982 1.0000
2.000 0.5147 0.00906 0.00323 -0.0542 0.7284 1.0000
2.250 0.5377 0.00944 0.00327 -0.0527 0.6713 1.0000
2.500 0.5599 0.00980 0.00338 -0.0512 0.6167 1.0000
2.750 0.5816 0.01020 0.00350 -0.0497 0.5631 1.0000
3.000 0.6034 0.01061 0.00365 -0.0482 0.5115 1.0000
3.250 0.6255 0.01103 0.00384 -0.0470 0.4664 1.0000
3.500 0.6482 0.01143 0.00403 -0.0458 0.4301 1.0000
3.750 0.6713 0.01181 0.00427 -0.0448 0.4012 1.0000
4.000 0.6944 0.01219 0.00450 -0.0438 0.3751 1.0000
4.250 0.7176 0.01259 0.00474 -0.0429 0.3522 1.0000
4.500 0.7413 0.01297 0.00503 -0.0420 0.3344 1.0000
4.750 0.7653 0.01333 0.00535 -0.0412 0.3187 1.0000
5.000 0.7894 0.01368 0.00567 -0.0405 0.3037 1.0000
5.250 0.8136 0.01401 0.00598 -0.0397 0.2888 1.0000
5.500 0.8377 0.01432 0.00631 -0.0390 0.2739 1.0000
5.750 0.8620 0.01459 0.00661 -0.0383 0.2576 1.0000
6.000 0.8864 0.01483 0.00690 -0.0376 0.2390 1.0000
6.250 0.9103 0.01512 0.00719 -0.0368 0.2176 1.0000
6.500 0.9336 0.01549 0.00753 -0.0360 0.1873 1.0000
6.750 0.9553 0.01616 0.00801 -0.0350 0.1465 1.0000
7.000 0.9758 0.01707 0.00874 -0.0338 0.1193 1.0000
7.250 0.9961 0.01800 0.00957 -0.0325 0.1038 1.0000
7.500 1.0173 0.01882 0.01041 -0.0314 0.0930 1.0000
7.750 1.0378 0.01975 0.01136 -0.0302 0.0844 1.0000
8.000 1.0566 0.02093 0.01247 -0.0288 0.0768 1.0000
8.250 1.0784 0.02168 0.01336 -0.0278 0.0706 1.0000
8.500 1.0961 0.02319 0.01480 -0.0264 0.0643 1.0000
8.750 1.1174 0.02394 0.01576 -0.0252 0.0592 1.0000
9.000 1.1356 0.02528 0.01707 -0.0239 0.0542 1.0000
9.250 1.1545 0.02665 0.01862 -0.0225 0.0498 1.0000
9.500 1.1732 0.02774 0.01980 -0.0212 0.0460 1.0000
9.750 1.1893 0.03031 0.02240 -0.0199 0.0428 1.0000
10.000 1.2066 0.03142 0.02381 -0.0182 0.0405 1.0000
10.250 1.2228 0.03268 0.02524 -0.0166 0.0379 1.0000
10.500 1.2384 0.03405 0.02665 -0.0152 0.0359 1.0000
10.750 1.2494 0.03764 0.03040 -0.0136 0.0343 1.0000
11.000 1.2584 0.03950 0.03263 -0.0112 0.0334 1.0000
11.250 1.2637 0.04187 0.03538 -0.0086 0.0325 1.0000
11.500 1.2658 0.04431 0.03814 -0.0058 0.0315 1.0000
11.750 1.2656 0.04661 0.04069 -0.0030 0.0306 1.0000
12.000 1.2637 0.04851 0.04276 0.0001 0.0298 1.0000
12.250 1.2591 0.05059 0.04498 0.0029 0.0291 1.0000
12.500 1.2520 0.05311 0.04766 0.0053 0.0286 1.0000
12.750 1.2416 0.05630 0.05103 0.0070 0.0283 1.0000
13.000 1.2265 0.06026 0.05521 0.0078 0.0281 1.0000
13.250 1.2073 0.06511 0.06030 0.0073 0.0281 1.0000
13.500 1.1835 0.07129 0.06675 0.0046 0.0282 1.0000
13.750 1.1435 0.08145 0.07729 -0.0021 0.0289 1.0000
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Polar data table (+)
Polar graphs
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