GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 344 (PFALZ 71) AIRFOIL (goe344-il) Reynolds number: 500,000 Max Cl/Cd: 77.11 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe344-il-500000-n5.txt Download as CSV file: xf-goe344-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.9052 0.03097 0.02753 -0.0474 1.0000 0.0120
-10.500 -0.8948 0.02701 0.02316 -0.0469 1.0000 0.0125
-10.250 -0.8792 0.02465 0.02047 -0.0460 1.0000 0.0131
-10.000 -0.8593 0.02341 0.01910 -0.0452 1.0000 0.0138
-9.750 -0.8367 0.02287 0.01851 -0.0444 1.0000 0.0145
-9.500 -0.8143 0.02226 0.01782 -0.0437 1.0000 0.0153
-9.250 -0.7928 0.02138 0.01679 -0.0428 1.0000 0.0162
-9.000 -0.7717 0.02032 0.01549 -0.0418 1.0000 0.0170
-8.750 -0.7498 0.01951 0.01456 -0.0409 1.0000 0.0177
-8.500 -0.7264 0.01922 0.01424 -0.0402 1.0000 0.0184
-8.250 -0.7027 0.01901 0.01399 -0.0394 1.0000 0.0192
-8.000 -0.6794 0.01867 0.01359 -0.0386 1.0000 0.0202
-7.750 -0.6566 0.01814 0.01294 -0.0377 1.0000 0.0212
-7.500 -0.6337 0.01761 0.01223 -0.0367 1.0000 0.0221
-7.250 -0.6104 0.01719 0.01168 -0.0358 1.0000 0.0226
-7.000 -0.5886 0.01628 0.01066 -0.0349 1.0000 0.0237
-6.750 -0.5654 0.01593 0.01028 -0.0340 1.0000 0.0245
-6.500 -0.5422 0.01559 0.00988 -0.0331 1.0000 0.0253
-6.250 -0.5189 0.01522 0.00945 -0.0322 1.0000 0.0262
-6.000 -0.4882 0.01478 0.00891 -0.0329 0.9990 0.0273
-5.750 -0.4550 0.01429 0.00830 -0.0341 0.9974 0.0282
-5.500 -0.4205 0.01389 0.00779 -0.0356 0.9957 0.0290
-5.250 -0.3855 0.01348 0.00729 -0.0371 0.9940 0.0295
-5.000 -0.3533 0.01269 0.00639 -0.0381 0.9915 0.0304
-4.750 -0.3215 0.01210 0.00576 -0.0390 0.9894 0.0316
-4.500 -0.2894 0.01171 0.00532 -0.0399 0.9877 0.0326
-4.250 -0.2565 0.01134 0.00491 -0.0410 0.9861 0.0333
-4.000 -0.2249 0.01100 0.00453 -0.0418 0.9831 0.0340
-3.750 -0.1919 0.01066 0.00416 -0.0428 0.9791 0.0348
-3.250 -0.1257 0.01004 0.00349 -0.0449 0.9692 0.0367
-3.000 -0.0915 0.00977 0.00320 -0.0461 0.9645 0.0378
-2.750 -0.0617 0.00950 0.00291 -0.0463 0.9557 0.0395
-2.500 -0.0281 0.00921 0.00264 -0.0474 0.9474 0.0427
-2.000 0.0458 0.00866 0.00214 -0.0511 0.9198 0.0584
-1.750 0.0792 0.00848 0.00196 -0.0521 0.9000 0.0737
-1.500 0.1089 0.00837 0.00183 -0.0523 0.8766 0.0864
-1.250 0.1363 0.00833 0.00174 -0.0519 0.8400 0.0990
-1.000 0.1611 0.00845 0.00165 -0.0509 0.7695 0.1111
-0.750 0.1856 0.00865 0.00162 -0.0499 0.7136 0.1225
-0.500 0.2113 0.00879 0.00162 -0.0493 0.6740 0.1348
-0.250 0.2376 0.00889 0.00161 -0.0489 0.6394 0.1445
0.000 0.2639 0.00898 0.00160 -0.0485 0.6054 0.1534
0.250 0.2901 0.00908 0.00160 -0.0481 0.5701 0.1653
0.500 0.3165 0.00916 0.00161 -0.0477 0.5380 0.1809
0.750 0.3431 0.00922 0.00164 -0.0474 0.5107 0.2016
1.000 0.3695 0.00924 0.00170 -0.0471 0.4812 0.2488
1.250 0.3958 0.00930 0.00176 -0.0468 0.4477 0.2967
1.500 0.4220 0.00934 0.00183 -0.0465 0.4123 0.3523
1.750 0.4346 0.00795 0.00196 -0.0431 0.3835 0.9329
2.000 0.4703 0.00820 0.00210 -0.0446 0.3520 0.9766
2.250 0.5068 0.00844 0.00222 -0.0466 0.3312 0.9884
2.500 0.5437 0.00866 0.00235 -0.0486 0.3142 0.9950
2.750 0.5842 0.00887 0.00249 -0.0515 0.2998 0.9996
3.000 0.6103 0.00903 0.00259 -0.0511 0.2859 1.0000
3.250 0.6347 0.00923 0.00269 -0.0503 0.2684 1.0000
3.500 0.6591 0.00941 0.00281 -0.0496 0.2523 1.0000
3.750 0.6838 0.00957 0.00292 -0.0489 0.2395 1.0000
4.000 0.7086 0.00974 0.00305 -0.0482 0.2279 1.0000
4.250 0.7332 0.00991 0.00319 -0.0475 0.2176 1.0000
4.500 0.7578 0.01011 0.00335 -0.0468 0.2053 1.0000
4.750 0.7823 0.01033 0.00351 -0.0461 0.1914 1.0000
5.000 0.8069 0.01056 0.00370 -0.0454 0.1772 1.0000
5.250 0.8315 0.01081 0.00390 -0.0448 0.1618 1.0000
5.500 0.8559 0.01110 0.00413 -0.0441 0.1430 1.0000
5.750 0.8798 0.01149 0.00441 -0.0434 0.1211 1.0000
6.000 0.9037 0.01190 0.00473 -0.0427 0.1000 1.0000
6.250 0.9275 0.01233 0.00508 -0.0420 0.0838 1.0000
6.500 0.9517 0.01272 0.00544 -0.0414 0.0728 1.0000
6.750 0.9761 0.01309 0.00580 -0.0408 0.0655 1.0000
7.000 1.0002 0.01350 0.00620 -0.0402 0.0586 1.0000
7.250 1.0247 0.01386 0.00657 -0.0396 0.0539 1.0000
7.500 1.0491 0.01422 0.00695 -0.0390 0.0496 1.0000
7.750 1.0728 0.01467 0.00740 -0.0384 0.0454 1.0000
8.000 1.0973 0.01500 0.00780 -0.0378 0.0429 1.0000
8.250 1.1214 0.01538 0.00821 -0.0372 0.0396 1.0000
8.500 1.1448 0.01585 0.00868 -0.0366 0.0360 1.0000
8.750 1.1687 0.01623 0.00912 -0.0360 0.0332 1.0000
9.000 1.1917 0.01670 0.00959 -0.0353 0.0290 1.0000
9.250 1.2147 0.01717 0.01011 -0.0346 0.0252 1.0000
9.500 1.2368 0.01774 0.01068 -0.0338 0.0210 1.0000
9.750 1.2583 0.01835 0.01131 -0.0329 0.0176 1.0000
10.000 1.2792 0.01901 0.01201 -0.0319 0.0153 1.0000
10.250 1.2997 0.01969 0.01275 -0.0308 0.0136 1.0000
10.500 1.3188 0.02050 0.01362 -0.0296 0.0122 1.0000
10.750 1.3382 0.02122 0.01446 -0.0284 0.0114 1.0000
11.000 1.3571 0.02197 0.01531 -0.0272 0.0108 1.0000
11.250 1.3748 0.02278 0.01622 -0.0258 0.0102 1.0000
11.500 1.3913 0.02368 0.01721 -0.0243 0.0096 1.0000
11.750 1.4054 0.02473 0.01835 -0.0225 0.0090 1.0000
12.000 1.4179 0.02584 0.01958 -0.0205 0.0086 1.0000
12.250 1.4313 0.02678 0.02064 -0.0187 0.0083 1.0000
12.500 1.4423 0.02779 0.02179 -0.0165 0.0079 1.0000
12.750 1.4492 0.02886 0.02298 -0.0137 0.0077 1.0000
13.000 1.4545 0.03006 0.02429 -0.0108 0.0074 1.0000
13.250 1.4583 0.03143 0.02578 -0.0081 0.0072 1.0000
13.500 1.4608 0.03298 0.02746 -0.0056 0.0070 1.0000
13.750 1.4611 0.03483 0.02944 -0.0034 0.0068 1.0000
14.000 1.4590 0.03705 0.03179 -0.0016 0.0067 1.0000
14.250 1.4542 0.03979 0.03468 -0.0004 0.0066 1.0000
14.500 1.4463 0.04327 0.03831 -0.0001 0.0065 1.0000
14.750 1.4349 0.04780 0.04301 -0.0012 0.0064 1.0000
15.000 1.4219 0.05328 0.04866 -0.0037 0.0063 1.0000
15.250 1.4097 0.05914 0.05471 -0.0068 0.0063 1.0000
15.500 1.3933 0.06606 0.06181 -0.0106 0.0063 1.0000
15.750 1.3729 0.07379 0.06971 -0.0147 0.0063 1.0000
16.000 1.3500 0.08206 0.07813 -0.0189 0.0063 1.0000
16.250 1.3247 0.09063 0.08685 -0.0231 0.0063 1.0000
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