GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 673 AIRFOIL (goe673-il) Reynolds number: 50,000 Max Cl/Cd: 37.52 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe673-il-50000-n5.txt Download as CSV file: xf-goe673-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 673 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4370 0.09912 0.09235 -0.0453 1.0000 0.0394
-9.250 -0.4361 0.09540 0.08869 -0.0457 1.0000 0.0391
-9.000 -0.4381 0.09151 0.08487 -0.0466 1.0000 0.0388
-8.750 -0.4427 0.08758 0.08103 -0.0476 1.0000 0.0384
-8.500 -0.4504 0.08371 0.07727 -0.0485 1.0000 0.0381
-8.250 -0.4614 0.07982 0.07348 -0.0494 1.0000 0.0376
-8.000 -0.4717 0.07564 0.06937 -0.0506 1.0000 0.0372
-7.750 -0.4824 0.07174 0.06548 -0.0510 1.0000 0.0367
-7.500 -0.4921 0.06784 0.06153 -0.0511 1.0000 0.0364
-7.250 -0.4996 0.06387 0.05746 -0.0510 1.0000 0.0361
-7.000 -0.5038 0.05987 0.05328 -0.0507 1.0000 0.0359
-6.750 -0.5041 0.05587 0.04900 -0.0504 1.0000 0.0359
-6.500 -0.4999 0.05198 0.04477 -0.0501 1.0000 0.0362
-6.250 -0.4915 0.04825 0.04062 -0.0496 1.0000 0.0365
-6.000 -0.4793 0.04471 0.03661 -0.0491 1.0000 0.0367
-5.750 -0.4637 0.04143 0.03283 -0.0486 1.0000 0.0368
-5.500 -0.4453 0.03848 0.02937 -0.0479 1.0000 0.0371
-5.250 -0.4247 0.03590 0.02628 -0.0472 1.0000 0.0376
-5.000 -0.4025 0.03376 0.02365 -0.0464 1.0000 0.0387
-4.750 -0.3808 0.03172 0.02140 -0.0458 1.0000 0.0415
-4.500 -0.3587 0.03022 0.01970 -0.0452 1.0000 0.0450
-4.250 -0.3353 0.02884 0.01800 -0.0443 1.0000 0.0477
-4.000 -0.3116 0.02767 0.01657 -0.0435 1.0000 0.0511
-3.750 -0.2879 0.02650 0.01531 -0.0434 1.0000 0.0602
-3.500 -0.2613 0.02541 0.01407 -0.0437 0.9994 0.0718
-3.250 -0.2222 0.02339 0.01280 -0.0470 0.9958 0.1912
-3.000 -0.1908 0.02196 0.01288 -0.0485 0.9911 0.5005
-2.750 -0.1613 0.02165 0.01293 -0.0482 0.9850 0.6242
-2.500 -0.1291 0.02154 0.01271 -0.0487 0.9781 0.6967
-2.250 -0.1004 0.02140 0.01250 -0.0483 0.9704 0.7678
-2.000 -0.0694 0.02128 0.01232 -0.0480 0.9630 0.8542
-1.750 -0.0164 0.02118 0.01194 -0.0531 0.9550 1.0000
-1.500 0.0189 0.02132 0.01166 -0.0557 0.9456 1.0000
-1.250 0.0582 0.02150 0.01149 -0.0588 0.9379 1.0000
-1.000 0.0935 0.02168 0.01138 -0.0610 0.9285 1.0000
-0.750 0.1272 0.02186 0.01130 -0.0628 0.9188 1.0000
-0.500 0.1658 0.02202 0.01124 -0.0655 0.9109 1.0000
-0.250 0.1992 0.02219 0.01124 -0.0671 0.9008 1.0000
0.000 0.2314 0.02237 0.01125 -0.0684 0.8905 1.0000
0.250 0.2689 0.02250 0.01126 -0.0706 0.8822 1.0000
0.500 0.3025 0.02263 0.01129 -0.0720 0.8724 1.0000
0.750 0.3322 0.02279 0.01138 -0.0726 0.8614 1.0000
1.000 0.3633 0.02293 0.01147 -0.0735 0.8510 1.0000
1.250 0.3994 0.02296 0.01147 -0.0750 0.8427 1.0000
1.500 0.4282 0.02310 0.01161 -0.0754 0.8313 1.0000
1.750 0.4563 0.02326 0.01178 -0.0755 0.8197 1.0000
2.000 0.4852 0.02340 0.01196 -0.0758 0.8084 1.0000
2.250 0.5163 0.02346 0.01207 -0.0763 0.7981 1.0000
2.500 0.5485 0.02347 0.01214 -0.0769 0.7881 1.0000
2.750 0.5753 0.02364 0.01241 -0.0767 0.7755 1.0000
3.000 0.6026 0.02378 0.01265 -0.0765 0.7630 1.0000
3.250 0.6305 0.02391 0.01288 -0.0764 0.7507 1.0000
3.500 0.6590 0.02401 0.01314 -0.0763 0.7383 1.0000
3.750 0.6880 0.02408 0.01335 -0.0762 0.7259 1.0000
4.000 0.7170 0.02414 0.01357 -0.0761 0.7132 1.0000
4.250 0.7456 0.02422 0.01386 -0.0758 0.6999 1.0000
4.500 0.7733 0.02434 0.01418 -0.0754 0.6858 1.0000
4.750 0.8004 0.02451 0.01456 -0.0749 0.6711 1.0000
5.000 0.8270 0.02472 0.01500 -0.0743 0.6559 1.0000
5.250 0.8534 0.02497 0.01556 -0.0737 0.6404 1.0000
5.500 0.8797 0.02526 0.01615 -0.0731 0.6249 1.0000
5.750 0.9059 0.02560 0.01684 -0.0724 0.6093 1.0000
6.000 0.9216 0.02473 0.01591 -0.0676 0.5509 1.0000
6.250 0.9253 0.02466 0.01540 -0.0616 0.4558 1.0000
6.500 0.9238 0.02589 0.01583 -0.0562 0.3131 1.0000
6.750 0.9068 0.02970 0.01775 -0.0511 0.0938 1.0000
7.000 0.9091 0.03234 0.02009 -0.0480 0.0668 1.0000
7.250 0.9145 0.03430 0.02225 -0.0452 0.0565 1.0000
7.500 0.9200 0.03619 0.02430 -0.0425 0.0497 1.0000
7.750 0.9250 0.03815 0.02641 -0.0400 0.0454 1.0000
8.000 0.9279 0.04038 0.02875 -0.0375 0.0430 1.0000
8.250 0.9368 0.04230 0.03086 -0.0353 0.0406 1.0000
8.500 0.9503 0.04406 0.03284 -0.0335 0.0373 1.0000
8.750 0.9684 0.04594 0.03479 -0.0320 0.0341 1.0000
9.000 1.0148 0.04827 0.03726 -0.0324 0.0322 1.0000
9.250 1.0562 0.05133 0.04074 -0.0332 0.0308 1.0000
9.500 1.0779 0.05437 0.04420 -0.0324 0.0292 1.0000
9.750 1.0902 0.05738 0.04758 -0.0308 0.0279 1.0000
10.000 1.0969 0.06048 0.05101 -0.0288 0.0271 1.0000
10.250 1.0989 0.06376 0.05465 -0.0265 0.0268 1.0000
10.500 1.0957 0.06715 0.05838 -0.0241 0.0268 1.0000
10.750 1.0882 0.07066 0.06235 -0.0218 0.0268 1.0000
11.000 1.0773 0.07435 0.06635 -0.0199 0.0269 1.0000
11.250 1.0636 0.07832 0.07060 -0.0186 0.0270 1.0000
11.500 1.0480 0.08262 0.07517 -0.0181 0.0272 1.0000
11.750 1.0305 0.08736 0.08015 -0.0184 0.0274 1.0000
12.000 1.0118 0.09261 0.08563 -0.0196 0.0276 1.0000
12.250 0.9921 0.09846 0.09167 -0.0219 0.0278 1.0000
12.500 0.9722 0.10497 0.09823 -0.0251 0.0281 1.0000
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Polar data table (+)
Polar graphs
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