GOE 571 AIRFOIL (goe571-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 571 AIRFOIL (goe571-il) Reynolds number: 500,000 Max Cl/Cd: 42.76 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe571-il-500000-n5.txt Download as CSV file: xf-goe571-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 571 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
------ -------- --------- --------- -------- -------- --------
-12.750 0.4922 0.10463 0.09930 -0.1670 0.5382 0.0257
-12.500 0.4917 0.10179 0.09644 -0.1684 0.5352 0.0258
-12.250 0.4970 0.09932 0.09397 -0.1693 0.5324 0.0258
-12.000 0.5006 0.09668 0.09134 -0.1704 0.5291 0.0259
-11.750 0.5053 0.09412 0.08877 -0.1713 0.5247 0.0259
-11.500 0.5132 0.09198 0.08662 -0.1717 0.5212 0.0260
-11.250 0.5258 0.09053 0.08514 -0.1716 0.5162 0.0261
-11.000 0.5383 0.08910 0.08371 -0.1716 0.5122 0.0263
-10.750 0.5463 0.08722 0.08184 -0.1719 0.5083 0.0266
-10.500 0.5528 0.08532 0.07993 -0.1723 0.5041 0.0267
-10.250 0.5592 0.08353 0.07812 -0.1725 0.5000 0.0270
-10.000 0.5636 0.08153 0.07610 -0.1727 0.4961 0.0273
-9.750 0.5674 0.07938 0.07398 -0.1731 0.4928 0.0279
-9.500 0.5708 0.07731 0.07191 -0.1733 0.4893 0.0277
-9.250 0.5717 0.07505 0.06966 -0.1734 0.4854 0.0282
-9.000 0.5485 0.06980 0.06444 -0.1754 0.4839 0.0294
-8.750 0.5499 0.06796 0.06260 -0.1748 0.4803 0.0293
-8.500 0.5383 0.06452 0.05919 -0.1751 0.4776 0.0294
-8.250 0.5121 0.05902 0.05372 -0.1750 0.4762 0.0259
-8.000 0.5052 0.05686 0.05161 -0.1743 0.4732 0.0258
-7.750 0.5031 0.05579 0.05056 -0.1729 0.4695 0.0256
-7.500 0.4841 0.05346 0.04827 -0.1720 0.4669 0.0255
-7.250 0.4573 0.05142 0.04624 -0.1682 0.4644 0.0253
-7.000 0.4216 0.04988 0.04470 -0.1611 0.4616 0.0251
-6.750 0.3896 0.04822 0.04304 -0.1539 0.4594 0.0250
-6.500 0.3655 0.04614 0.04093 -0.1480 0.4576 0.0247
-6.250 0.3413 0.04394 0.03868 -0.1416 0.4551 0.0246
-6.000 0.3169 0.04131 0.03596 -0.1349 0.4530 0.0247
-5.750 0.2990 0.03893 0.03346 -0.1287 0.4506 0.0248
-5.500 0.2831 0.03671 0.03110 -0.1223 0.4482 0.0246
-5.250 0.2673 0.03424 0.02845 -0.1157 0.4458 0.0242
-5.000 0.2483 0.03123 0.02517 -0.1081 0.4437 0.0241
-4.500 0.2280 0.02655 0.01990 -0.0951 0.4399 0.0242
-4.250 0.2297 0.02532 0.01846 -0.0904 0.4376 0.0242
-4.000 0.2335 0.02429 0.01720 -0.0861 0.4352 0.0245
-3.750 0.2412 0.02357 0.01632 -0.0824 0.4327 0.0244
-3.500 0.2488 0.02293 0.01550 -0.0787 0.4302 0.0245
-3.250 0.2576 0.02246 0.01488 -0.0752 0.4279 0.0247
-3.000 0.2667 0.02198 0.01424 -0.0718 0.4254 0.0248
-2.750 0.2777 0.02156 0.01367 -0.0687 0.4232 0.0248
-2.500 0.2915 0.02117 0.01318 -0.0661 0.4214 0.0250
-2.250 0.3059 0.02088 0.01278 -0.0636 0.4195 0.0251
-2.000 0.3199 0.02057 0.01237 -0.0611 0.4171 0.0252
-1.750 0.3339 0.02032 0.01202 -0.0586 0.4150 0.0253
-1.500 0.3475 0.02025 0.01184 -0.0561 0.4127 0.0256
-1.250 0.3611 0.02026 0.01173 -0.0536 0.4105 0.0258
-1.000 0.3748 0.02013 0.01153 -0.0513 0.4085 0.0258
-0.750 0.3890 0.01999 0.01133 -0.0491 0.4065 0.0261
-0.500 0.4062 0.01982 0.01114 -0.0474 0.4050 0.0262
-0.250 0.4238 0.01976 0.01106 -0.0458 0.4037 0.0262
0.000 0.4410 0.01970 0.01100 -0.0442 0.4021 0.0263
0.250 0.4582 0.01967 0.01097 -0.0426 0.4006 0.0267
0.500 0.4754 0.01969 0.01098 -0.0410 0.3988 0.0267
0.750 0.4916 0.01976 0.01104 -0.0394 0.3970 0.0270
1.000 0.5076 0.01987 0.01113 -0.0378 0.3951 0.0271
1.250 0.5241 0.01999 0.01123 -0.0363 0.3933 0.0274
1.500 0.5402 0.02017 0.01139 -0.0348 0.3916 0.0276
1.750 0.5558 0.02040 0.01160 -0.0333 0.3896 0.0278
2.000 0.5739 0.02059 0.01177 -0.0322 0.3881 0.0280
2.250 0.5936 0.02075 0.01195 -0.0314 0.3869 0.0283
2.500 0.6130 0.02097 0.01219 -0.0306 0.3857 0.0287
2.750 0.6325 0.02123 0.01245 -0.0299 0.3842 0.0290
3.000 0.6525 0.02149 0.01273 -0.0294 0.3825 0.0293
3.250 0.6723 0.02180 0.01305 -0.0289 0.3809 0.0296
3.500 0.6932 0.02212 0.01338 -0.0288 0.3794 0.0299
3.750 0.7142 0.02247 0.01376 -0.0287 0.3777 0.0310
4.000 0.7343 0.02289 0.01418 -0.0285 0.3762 0.0312
4.250 0.7542 0.02336 0.01464 -0.0283 0.3748 0.0324
4.500 0.7747 0.02383 0.01509 -0.0283 0.3732 0.0331
4.750 0.7962 0.02428 0.01552 -0.0284 0.3716 0.0333
5.000 0.8190 0.02475 0.01602 -0.0289 0.3704 0.0345
5.250 0.8391 0.02530 0.01661 -0.0290 0.3690 0.0344
5.750 0.8827 0.02642 0.01779 -0.0299 0.3662 0.0394
6.000 0.9068 0.02702 0.01847 -0.0310 0.3647 0.0528
6.500 1.2089 0.02827 0.02194 -0.0849 0.3598 1.0000
6.750 1.2214 0.02913 0.02277 -0.0839 0.3582 1.0000
7.000 1.2330 0.03007 0.02368 -0.0829 0.3566 1.0000
7.250 1.2459 0.03093 0.02451 -0.0820 0.3549 1.0000
7.500 1.2595 0.03180 0.02540 -0.0813 0.3540 1.0000
7.750 1.2709 0.03284 0.02648 -0.0804 0.3524 1.0000
8.000 1.2834 0.03383 0.02748 -0.0797 0.3510 1.0000
8.250 1.2951 0.03487 0.02855 -0.0789 0.3495 1.0000
8.500 1.3056 0.03603 0.02973 -0.0781 0.3477 1.0000
8.750 1.3161 0.03718 0.03088 -0.0774 0.3458 1.0000
9.000 1.3259 0.03841 0.03210 -0.0766 0.3442 1.0000
9.250 1.3349 0.03969 0.03338 -0.0758 0.3421 1.0000
9.500 1.3456 0.04084 0.03450 -0.0751 0.3405 1.0000
9.750 1.3542 0.04220 0.03588 -0.0744 0.3386 1.0000
10.000 1.3633 0.04357 0.03730 -0.0738 0.3371 1.0000
10.250 1.3726 0.04494 0.03872 -0.0732 0.3357 1.0000
10.500 1.3792 0.04654 0.04035 -0.0725 0.3337 1.0000
10.750 1.3865 0.04809 0.04192 -0.0719 0.3314 1.0000
11.000 1.3928 0.04973 0.04358 -0.0712 0.3294 1.0000
11.250 1.3994 0.05134 0.04519 -0.0706 0.3273 1.0000
11.500 1.4083 0.05274 0.04658 -0.0701 0.3256 1.0000
11.750 1.4140 0.05446 0.04832 -0.0695 0.3235 1.0000
12.000 1.4189 0.05632 0.05025 -0.0690 0.3219 1.0000
12.250 1.4206 0.05848 0.05247 -0.0683 0.3190 1.0000
12.500 1.4228 0.06062 0.05466 -0.0677 0.3168 1.0000
12.750 1.4271 0.06254 0.05660 -0.0672 0.3144 1.0000
13.000 1.4321 0.06440 0.05846 -0.0668 0.3124 1.0000
13.250 1.4372 0.06622 0.06027 -0.0663 0.3101 1.0000
13.500 1.4384 0.06851 0.06263 -0.0658 0.3080 1.0000
13.750 1.4332 0.07149 0.06570 -0.0651 0.3051 1.0000
14.000 1.4299 0.07429 0.06855 -0.0645 0.3015 1.0000
14.250 1.4296 0.07677 0.07105 -0.0640 0.2988 1.0000
14.500 1.4336 0.07879 0.07306 -0.0638 0.2963 1.0000
14.750 1.4334 0.08130 0.07562 -0.0634 0.2940 1.0000
15.000 1.4204 0.08526 0.07968 -0.0627 0.2903 1.0000
15.250 1.4133 0.08855 0.08301 -0.0622 0.2861 1.0000
15.500 1.4153 0.09086 0.08533 -0.0620 0.2841 1.0000
15.750 1.4110 0.09388 0.08836 -0.0617 0.2798 1.0000
16.000 1.3936 0.09848 0.09306 -0.0611 0.2753 1.0000
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