GOE 442 AIRFOIL (goe442-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 442 AIRFOIL (goe442-il) Reynolds number: 200,000 Max Cl/Cd: 73.41 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe442-il-200000.txt Download as CSV file: xf-goe442-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 442 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3582 0.08829 0.08495 -0.0215 1.0000 0.0386
-7.250 -0.3649 0.08636 0.08308 -0.0199 1.0000 0.0391
-7.000 -0.3689 0.08407 0.08085 -0.0193 1.0000 0.0398
-6.750 -0.3707 0.08153 0.07836 -0.0194 1.0000 0.0408
-6.500 -0.3713 0.07888 0.07574 -0.0201 1.0000 0.0417
-6.250 -0.3693 0.07597 0.07285 -0.0219 1.0000 0.0430
-6.000 -0.3558 0.07237 0.06920 -0.0304 1.0000 0.0447
-5.750 -0.3413 0.06848 0.06518 -0.0351 1.0000 0.0451
-5.500 -0.3370 0.06295 0.05963 -0.0361 1.0000 0.0456
-5.250 -0.3350 0.05998 0.05673 -0.0334 1.0000 0.0464
-5.000 -0.3282 0.05765 0.05442 -0.0317 1.0000 0.0474
-4.750 -0.3185 0.05538 0.05215 -0.0310 1.0000 0.0491
-4.500 -0.2899 0.05172 0.04837 -0.0351 0.9979 0.0529
-4.250 -0.2345 0.04385 0.03995 -0.0466 0.9933 0.0585
-4.000 -0.2029 0.04085 0.03697 -0.0493 0.9882 0.0606
-3.750 -0.1610 0.03746 0.03336 -0.0541 0.9841 0.0658
-3.500 -0.1209 0.03278 0.02815 -0.0583 0.9778 0.0732
-3.250 -0.0795 0.03022 0.02525 -0.0620 0.9728 0.0866
-3.000 -0.0359 0.02385 0.01790 -0.0634 0.9696 0.0553
-2.750 0.0021 0.02234 0.01583 -0.0646 0.9621 0.0573
-2.500 0.0418 0.01904 0.01214 -0.0671 0.9584 0.0595
-2.250 0.0781 0.01791 0.01092 -0.0685 0.9510 0.0650
-2.000 0.1202 0.01693 0.00964 -0.0707 0.9452 0.0698
-1.750 0.1590 0.01550 0.00816 -0.0726 0.9389 0.0767
-1.500 0.1987 0.01465 0.00724 -0.0744 0.9314 0.0825
-1.250 0.2410 0.01357 0.00619 -0.0769 0.9257 0.0893
-1.000 0.2776 0.01286 0.00551 -0.0781 0.9160 0.0966
-0.750 0.3117 0.01213 0.00487 -0.0788 0.9042 0.1068
-0.500 0.3461 0.01153 0.00432 -0.0795 0.8906 0.1206
-0.250 0.3788 0.01071 0.00393 -0.0800 0.8740 0.2160
0.000 0.4443 0.00852 0.00365 -0.0874 0.8578 1.0000
0.250 0.4773 0.00840 0.00331 -0.0877 0.8276 1.0000
0.500 0.5074 0.00839 0.00306 -0.0875 0.7893 1.0000
0.750 0.5344 0.00853 0.00290 -0.0866 0.7447 1.0000
1.000 0.5585 0.00879 0.00283 -0.0853 0.6989 1.0000
1.250 0.5814 0.00908 0.00284 -0.0839 0.6584 1.0000
1.500 0.6042 0.00939 0.00288 -0.0826 0.6236 1.0000
1.750 0.6274 0.00969 0.00296 -0.0814 0.5953 1.0000
2.000 0.6509 0.01002 0.00307 -0.0803 0.5723 1.0000
2.250 0.6750 0.01030 0.00321 -0.0794 0.5527 1.0000
2.500 0.6992 0.01060 0.00337 -0.0785 0.5348 1.0000
2.750 0.7235 0.01089 0.00356 -0.0777 0.5182 1.0000
3.000 0.7478 0.01117 0.00374 -0.0768 0.5020 1.0000
3.250 0.7722 0.01143 0.00392 -0.0760 0.4870 1.0000
3.500 0.7968 0.01167 0.00411 -0.0753 0.4733 1.0000
3.750 0.8213 0.01191 0.00433 -0.0745 0.4600 1.0000
4.000 0.8458 0.01214 0.00453 -0.0738 0.4473 1.0000
4.250 0.8703 0.01238 0.00473 -0.0730 0.4349 1.0000
4.500 0.8945 0.01262 0.00493 -0.0722 0.4222 1.0000
4.750 0.9187 0.01283 0.00517 -0.0714 0.4084 1.0000
5.000 0.9425 0.01304 0.00539 -0.0706 0.3939 1.0000
5.250 0.9660 0.01328 0.00562 -0.0696 0.3782 1.0000
5.500 0.9893 0.01350 0.00586 -0.0687 0.3593 1.0000
5.750 1.0116 0.01378 0.00612 -0.0676 0.3364 1.0000
6.000 1.0330 0.01413 0.00641 -0.0664 0.3069 1.0000
6.250 1.0531 0.01462 0.00678 -0.0650 0.2679 1.0000
6.500 1.0720 0.01532 0.00726 -0.0635 0.2333 1.0000
6.750 1.0922 0.01600 0.00784 -0.0622 0.2127 1.0000
7.000 1.1127 0.01668 0.00845 -0.0609 0.2006 1.0000
7.250 1.1331 0.01739 0.00909 -0.0597 0.1915 1.0000
7.500 1.1550 0.01799 0.00975 -0.0587 0.1843 1.0000
7.750 1.1763 0.01870 0.01047 -0.0576 0.1790 1.0000
8.000 1.1982 0.01947 0.01126 -0.0567 0.1743 1.0000
8.250 1.2192 0.02002 0.01188 -0.0557 0.1667 1.0000
8.500 1.2388 0.02062 0.01252 -0.0545 0.1570 1.0000
8.750 1.2574 0.02135 0.01322 -0.0533 0.1480 1.0000
9.000 1.2775 0.02177 0.01382 -0.0521 0.1412 1.0000
9.250 1.2959 0.02260 0.01463 -0.0509 0.1345 1.0000
9.500 1.3146 0.02292 0.01517 -0.0495 0.1270 1.0000
9.750 1.3312 0.02358 0.01589 -0.0480 0.1195 1.0000
10.000 1.3474 0.02390 0.01638 -0.0464 0.1088 1.0000
10.250 1.3672 0.02389 0.01654 -0.0452 0.0833 1.0000
10.500 1.3715 0.02549 0.01778 -0.0420 0.0479 1.0000
10.750 1.3698 0.02726 0.01954 -0.0380 0.0407 1.0000
11.000 1.3722 0.02877 0.02119 -0.0346 0.0368 1.0000
11.250 1.3716 0.03050 0.02300 -0.0313 0.0339 1.0000
11.500 1.3638 0.03280 0.02537 -0.0277 0.0320 1.0000
11.750 1.3653 0.03460 0.02734 -0.0252 0.0304 1.0000
12.000 1.3651 0.03663 0.02954 -0.0231 0.0291 1.0000
12.250 1.3638 0.03891 0.03195 -0.0212 0.0282 1.0000
12.500 1.3615 0.04144 0.03459 -0.0197 0.0272 1.0000
12.750 1.3583 0.04424 0.03747 -0.0185 0.0263 1.0000
13.000 1.3553 0.04725 0.04057 -0.0176 0.0255 1.0000
13.250 1.3530 0.05059 0.04398 -0.0165 0.0248 1.0000
13.500 1.3517 0.05382 0.04737 -0.0160 0.0242 1.0000
13.750 1.3495 0.05699 0.05074 -0.0161 0.0237 1.0000
14.000 1.3457 0.06059 0.05454 -0.0165 0.0230 1.0000
14.250 1.3422 0.06433 0.05847 -0.0170 0.0227 1.0000
14.500 1.3364 0.06848 0.06281 -0.0179 0.0223 1.0000
14.750 1.3290 0.07301 0.06753 -0.0192 0.0219 1.0000
15.000 1.3204 0.07790 0.07262 -0.0208 0.0217 1.0000
15.250 1.3098 0.08328 0.07820 -0.0230 0.0216 1.0000
15.500 1.2975 0.08910 0.08424 -0.0256 0.0215 1.0000
15.750 1.2830 0.09555 0.09089 -0.0288 0.0215 1.0000
16.000 1.2674 0.10248 0.09802 -0.0325 0.0215 1.0000
16.250 1.2497 0.11011 0.10584 -0.0369 0.0216 1.0000
16.500 1.2300 0.11857 0.11450 -0.0421 0.0217 1.0000
16.750 1.2084 0.12794 0.12407 -0.0480 0.0220 1.0000
17.000 1.1840 0.13853 0.13485 -0.0549 0.0223 1.0000
17.250 1.1560 0.15089 0.14737 -0.0630 0.0228 1.0000
17.500 1.1226 0.16583 0.16244 -0.0726 0.0237 1.0000
17.750 1.0860 0.18371 0.18039 -0.0831 0.0249 1.0000
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Polar data table (+)
Polar graphs
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