GOE 599 AIRFOIL (goe599-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 599 AIRFOIL (goe599-il) Reynolds number: 200,000 Max Cl/Cd: 61.49 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe599-il-200000.txt Download as CSV file: xf-goe599-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 599 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4198 0.10344 0.09990 -0.0288 1.0000 0.0653
-10.500 -0.4391 0.09749 0.09399 -0.0334 1.0000 0.0683
-10.250 -0.5564 0.09948 0.09583 -0.0275 1.0000 0.0591
-10.000 -0.5440 0.09807 0.09441 -0.0257 1.0000 0.0617
-9.750 -0.4445 0.08440 0.08097 -0.0347 1.0000 0.0726
-9.500 -0.4443 0.08082 0.07740 -0.0348 1.0000 0.0747
-9.250 -0.4527 0.07599 0.07261 -0.0364 1.0000 0.0771
-7.750 -0.6757 0.04143 0.03640 -0.0415 1.0000 0.0479
-7.500 -0.6696 0.03551 0.03000 -0.0390 1.0000 0.0401
-7.250 -0.6626 0.02993 0.02336 -0.0358 1.0000 0.0366
-7.000 -0.6463 0.02727 0.02035 -0.0342 1.0000 0.0369
-6.750 -0.6279 0.02512 0.01798 -0.0328 1.0000 0.0379
-6.500 -0.6083 0.02386 0.01661 -0.0317 1.0000 0.0401
-6.250 -0.5876 0.02252 0.01506 -0.0305 1.0000 0.0423
-6.000 -0.5659 0.02111 0.01342 -0.0293 1.0000 0.0439
-5.750 -0.5438 0.02009 0.01219 -0.0281 1.0000 0.0455
-5.500 -0.5222 0.01829 0.01039 -0.0273 1.0000 0.0493
-5.250 -0.5002 0.01749 0.00955 -0.0264 1.0000 0.0533
-5.000 -0.4776 0.01677 0.00873 -0.0255 1.0000 0.0567
-4.750 -0.4549 0.01585 0.00788 -0.0250 1.0000 0.0632
-4.500 -0.4316 0.01533 0.00730 -0.0243 1.0000 0.0703
-4.250 -0.4082 0.01493 0.00694 -0.0238 1.0000 0.0818
-4.000 -0.3842 0.01433 0.00645 -0.0235 1.0000 0.1084
-3.750 -0.3589 0.01322 0.00592 -0.0240 1.0000 0.2049
-3.500 -0.3345 0.01278 0.00581 -0.0240 1.0000 0.2928
-3.250 -0.3103 0.01252 0.00578 -0.0239 1.0000 0.3572
-3.000 -0.2724 0.01215 0.00578 -0.0265 0.9966 0.4484
-2.750 -0.2342 0.01193 0.00583 -0.0290 0.9933 0.5313
-2.500 -0.1980 0.01175 0.00587 -0.0310 0.9885 0.6032
-2.250 -0.1604 0.01158 0.00596 -0.0330 0.9847 0.6733
-2.000 -0.1263 0.01144 0.00599 -0.0342 0.9794 0.7284
-1.750 -0.0918 0.01132 0.00603 -0.0354 0.9741 0.7818
-1.250 -0.0253 0.01118 0.00610 -0.0366 0.9621 0.8867
-1.000 0.0226 0.01112 0.00605 -0.0402 0.9578 0.9382
-0.750 0.0776 0.01102 0.00590 -0.0455 0.9521 0.9739
-0.500 0.1360 0.01092 0.00575 -0.0519 0.9484 0.9953
-0.250 0.1864 0.01078 0.00557 -0.0569 0.9449 1.0000
0.000 0.2230 0.01064 0.00539 -0.0589 0.9374 1.0000
0.250 0.2605 0.01046 0.00520 -0.0609 0.9304 1.0000
0.500 0.2938 0.01026 0.00498 -0.0619 0.9200 1.0000
0.750 0.3280 0.00995 0.00466 -0.0628 0.9080 1.0000
1.000 0.3588 0.00966 0.00436 -0.0629 0.8938 1.0000
1.250 0.3879 0.00947 0.00416 -0.0627 0.8798 1.0000
1.500 0.4158 0.00928 0.00394 -0.0622 0.8624 1.0000
1.750 0.4435 0.00911 0.00370 -0.0614 0.8401 1.0000
2.000 0.4685 0.00909 0.00362 -0.0603 0.8159 1.0000
2.250 0.4936 0.00914 0.00361 -0.0594 0.7948 1.0000
2.500 0.5178 0.00921 0.00365 -0.0583 0.7721 1.0000
2.750 0.5417 0.00930 0.00370 -0.0572 0.7462 1.0000
3.000 0.5648 0.00939 0.00373 -0.0558 0.7109 1.0000
3.250 0.5872 0.00955 0.00373 -0.0542 0.6632 1.0000
3.500 0.6071 0.00990 0.00375 -0.0522 0.5875 1.0000
3.750 0.6242 0.01054 0.00391 -0.0499 0.4894 1.0000
4.000 0.6384 0.01156 0.00429 -0.0473 0.3627 1.0000
4.250 0.6460 0.01360 0.00509 -0.0444 0.1382 1.0000
4.500 0.6674 0.01435 0.00568 -0.0432 0.1097 1.0000
4.750 0.6899 0.01493 0.00622 -0.0423 0.1002 1.0000
5.000 0.7123 0.01551 0.00683 -0.0413 0.0942 1.0000
5.250 0.7345 0.01612 0.00745 -0.0403 0.0894 1.0000
5.500 0.7544 0.01704 0.00833 -0.0390 0.0857 1.0000
5.750 0.7769 0.01776 0.00911 -0.0380 0.0832 1.0000
6.000 0.7997 0.01847 0.00988 -0.0371 0.0793 1.0000
6.250 0.8219 0.01937 0.01075 -0.0362 0.0750 1.0000
6.500 0.8444 0.02065 0.01206 -0.0354 0.0707 1.0000
6.750 0.8681 0.02145 0.01296 -0.0347 0.0660 1.0000
7.000 0.8915 0.02295 0.01440 -0.0342 0.0607 1.0000
7.250 0.9149 0.02431 0.01598 -0.0334 0.0556 1.0000
7.500 0.9381 0.02557 0.01734 -0.0327 0.0507 1.0000
7.750 0.9607 0.02832 0.02019 -0.0322 0.0460 1.0000
8.000 0.9818 0.02923 0.02139 -0.0309 0.0423 1.0000
8.250 1.0033 0.03079 0.02310 -0.0299 0.0395 1.0000
8.500 1.0232 0.03287 0.02525 -0.0292 0.0372 1.0000
8.750 1.0373 0.03575 0.02856 -0.0272 0.0352 1.0000
9.000 1.0513 0.03784 0.03108 -0.0250 0.0332 1.0000
9.250 1.0617 0.04094 0.03460 -0.0226 0.0323 1.0000
9.500 1.0674 0.04446 0.03853 -0.0199 0.0317 1.0000
9.750 1.0666 0.04866 0.04317 -0.0167 0.0317 1.0000
10.000 1.0588 0.05335 0.04829 -0.0131 0.0322 1.0000
10.250 1.0465 0.05788 0.05318 -0.0097 0.0326 1.0000
10.500 1.0289 0.06201 0.05757 -0.0061 0.0331 1.0000
10.750 1.0074 0.06594 0.06171 -0.0029 0.0335 1.0000
11.000 0.9855 0.07022 0.06618 -0.0012 0.0339 1.0000
11.250 0.9641 0.07502 0.07112 -0.0010 0.0344 1.0000
11.500 0.9429 0.08048 0.07670 -0.0023 0.0350 1.0000
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Polar data table (+)
Polar graphs
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