GOE 513 AIRFOIL (goe513-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 513 AIRFOIL (goe513-il) Reynolds number: 500,000 Max Cl/Cd: 75.41 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe513-il-500000.txt Download as CSV file: xf-goe513-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 513 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2361 0.08342 0.08099 -0.0941 0.9726 0.0486
-11.000 -0.4946 0.04269 0.03893 -0.1136 0.9552 0.0369
-10.750 -0.5030 0.04007 0.03614 -0.1096 0.9481 0.0367
-10.500 -0.5028 0.03707 0.03289 -0.1072 0.9427 0.0366
-10.250 -0.4907 0.03431 0.02988 -0.1065 0.9402 0.0365
-10.000 -0.4738 0.03204 0.02728 -0.1061 0.9386 0.0367
-9.750 -0.4800 0.03106 0.02612 -0.0999 0.9282 0.0368
-9.500 -0.4053 0.03866 0.03449 -0.1063 0.9289 0.0482
-9.250 -0.3866 0.03411 0.02998 -0.1075 0.9267 0.0497
-9.000 -0.3537 0.03289 0.02880 -0.1093 0.9252 0.0510
-8.500 -0.3746 0.02294 0.01702 -0.0959 0.9100 0.0375
-8.250 -0.3399 0.02132 0.01532 -0.0976 0.9082 0.0378
-8.000 -0.3036 0.02022 0.01421 -0.0996 0.9064 0.0385
-7.750 -0.2966 0.01967 0.01362 -0.0952 0.8960 0.0389
-7.500 -0.2630 0.01877 0.01267 -0.0963 0.8919 0.0395
-7.250 -0.2390 0.01803 0.01186 -0.0954 0.8849 0.0399
-7.000 -0.2151 0.01731 0.01107 -0.0945 0.8767 0.0403
-6.750 -0.1807 0.01654 0.01023 -0.0957 0.8707 0.0407
-6.500 -0.1564 0.01594 0.00955 -0.0948 0.8597 0.0411
-6.250 -0.1274 0.01541 0.00894 -0.0949 0.8495 0.0417
-6.000 -0.0933 0.01486 0.00831 -0.0960 0.8401 0.0421
-5.750 -0.0674 0.01440 0.00778 -0.0955 0.8276 0.0425
-5.500 -0.0400 0.01366 0.00700 -0.0954 0.8152 0.0434
-5.250 -0.0129 0.01325 0.00654 -0.0952 0.8021 0.0444
-5.000 0.0115 0.01298 0.00620 -0.0943 0.7890 0.0454
-4.750 0.0335 0.01274 0.00589 -0.0929 0.7759 0.0462
-4.500 0.0559 0.01253 0.00559 -0.0916 0.7628 0.0472
-4.250 0.0784 0.01236 0.00532 -0.0903 0.7498 0.0479
-4.000 0.0970 0.01211 0.00501 -0.0881 0.7366 0.0490
-3.750 0.1159 0.01189 0.00475 -0.0861 0.7231 0.0504
-3.500 0.1348 0.01177 0.00456 -0.0840 0.7082 0.0519
-3.250 0.1524 0.01168 0.00439 -0.0816 0.6920 0.0538
-3.000 0.1672 0.01157 0.00420 -0.0787 0.6726 0.0561
-2.750 0.1785 0.01146 0.00402 -0.0750 0.6460 0.0597
-2.500 0.1843 0.01147 0.00389 -0.0700 0.6113 0.0632
-2.000 0.1886 0.01103 0.00367 -0.0592 0.5592 0.1844
-1.750 0.2010 0.01117 0.00379 -0.0558 0.5434 0.2140
-1.250 0.2362 0.01147 0.00395 -0.0512 0.5234 0.2368
-1.000 0.2542 0.01157 0.00402 -0.0491 0.5156 0.2451
-0.750 0.2748 0.01171 0.00411 -0.0475 0.5093 0.2534
-0.500 0.2948 0.01175 0.00415 -0.0457 0.5032 0.2600
-0.250 0.3145 0.01185 0.00421 -0.0440 0.4971 0.2651
0.000 0.3354 0.01195 0.00426 -0.0424 0.4914 0.2703
0.250 0.3558 0.01202 0.00430 -0.0408 0.4857 0.2747
0.500 0.3746 0.01202 0.00432 -0.0389 0.4799 0.2806
0.750 0.3951 0.01216 0.00440 -0.0373 0.4743 0.2867
1.000 0.4157 0.01222 0.00446 -0.0357 0.4696 0.2922
1.250 0.4348 0.01219 0.00446 -0.0339 0.4643 0.2979
1.500 0.4540 0.01224 0.00449 -0.0321 0.4590 0.3020
1.750 0.4739 0.01233 0.00454 -0.0304 0.4540 0.3061
2.000 0.4936 0.01235 0.00457 -0.0287 0.4489 0.3102
2.250 0.5120 0.01236 0.00460 -0.0267 0.4434 0.3154
2.500 0.5300 0.01244 0.00465 -0.0247 0.4379 0.3211
2.750 0.5494 0.01248 0.00471 -0.0230 0.4323 0.3272
3.000 0.5681 0.01251 0.00476 -0.0212 0.4267 0.3341
3.250 0.5847 0.01260 0.00483 -0.0190 0.4202 0.3426
3.500 0.6036 0.01264 0.00491 -0.0172 0.4145 0.3531
3.750 0.6219 0.01267 0.00500 -0.0154 0.4081 0.3682
4.000 0.6376 0.01270 0.00509 -0.0131 0.4018 0.3976
4.250 0.8544 0.01283 0.00672 -0.0542 0.3810 0.9727
4.500 0.8896 0.01324 0.00709 -0.0559 0.3714 0.9811
4.750 0.9425 0.01355 0.00732 -0.0616 0.3600 0.9847
5.000 0.9873 0.01392 0.00757 -0.0656 0.3479 0.9897
5.250 1.0279 0.01418 0.00780 -0.0687 0.3367 0.9937
5.500 1.0706 0.01439 0.00794 -0.0723 0.3254 0.9971
5.750 1.1078 0.01469 0.00813 -0.0749 0.3142 1.0000
6.000 1.1201 0.01490 0.00834 -0.0721 0.3069 1.0000
6.250 1.1290 0.01524 0.00862 -0.0688 0.2996 1.0000
6.500 1.1410 0.01552 0.00888 -0.0660 0.2931 1.0000
6.750 1.1522 0.01583 0.00917 -0.0631 0.2872 1.0000
7.000 1.1611 0.01625 0.00953 -0.0599 0.2814 1.0000
7.250 1.1754 0.01652 0.00981 -0.0576 0.2769 1.0000
7.500 1.1877 0.01686 0.01014 -0.0551 0.2722 1.0000
7.750 1.1981 0.01729 0.01054 -0.0522 0.2678 1.0000
8.000 1.2095 0.01772 0.01095 -0.0496 0.2639 1.0000
8.250 1.2241 0.01804 0.01130 -0.0475 0.2610 1.0000
8.500 1.2373 0.01842 0.01169 -0.0453 0.2578 1.0000
8.750 1.2498 0.01885 0.01212 -0.0430 0.2547 1.0000
9.000 1.2607 0.01937 0.01262 -0.0405 0.2515 1.0000
9.250 1.2716 0.01993 0.01316 -0.0380 0.2482 1.0000
9.500 1.2866 0.02030 0.01359 -0.0362 0.2462 1.0000
9.750 1.3006 0.02074 0.01406 -0.0343 0.2441 1.0000
10.000 1.3140 0.02121 0.01457 -0.0324 0.2419 1.0000
10.250 1.3268 0.02173 0.01510 -0.0305 0.2396 1.0000
10.500 1.3386 0.02232 0.01570 -0.0284 0.2374 1.0000
10.750 1.3498 0.02299 0.01635 -0.0264 0.2350 1.0000
11.000 1.3623 0.02364 0.01701 -0.0245 0.2325 1.0000
11.250 1.3756 0.02418 0.01761 -0.0229 0.2310 1.0000
11.500 1.3890 0.02475 0.01824 -0.0212 0.2292 1.0000
11.750 1.4017 0.02537 0.01891 -0.0196 0.2274 1.0000
12.000 1.4137 0.02604 0.01963 -0.0180 0.2252 1.0000
12.250 1.4244 0.02680 0.02040 -0.0162 0.2227 1.0000
12.500 1.4341 0.02766 0.02125 -0.0145 0.2199 1.0000
12.750 1.4463 0.02846 0.02203 -0.0130 0.2172 1.0000
13.000 1.4570 0.02925 0.02292 -0.0115 0.2158 1.0000
13.250 1.4676 0.03010 0.02386 -0.0100 0.2137 1.0000
13.500 1.4785 0.03097 0.02479 -0.0087 0.2119 1.0000
13.750 1.4892 0.03188 0.02575 -0.0073 0.2101 1.0000
14.000 1.4988 0.03288 0.02680 -0.0060 0.2081 1.0000
14.250 1.5067 0.03401 0.02795 -0.0046 0.2057 1.0000
14.500 1.5157 0.03509 0.02902 -0.0033 0.2032 1.0000
14.750 1.5249 0.03621 0.03020 -0.0021 0.2012 1.0000
15.000 1.5327 0.03745 0.03155 -0.0010 0.1993 1.0000
15.250 1.5401 0.03876 0.03295 0.0000 0.1972 1.0000
15.500 1.5482 0.04004 0.03429 0.0010 0.1953 1.0000
15.750 1.5540 0.04153 0.03584 0.0020 0.1929 1.0000
16.000 1.5598 0.04304 0.03738 0.0030 0.1909 1.0000
16.250 1.5646 0.04461 0.03894 0.0040 0.1880 1.0000
16.500 1.5701 0.04624 0.04068 0.0048 0.1862 1.0000
16.750 1.5747 0.04803 0.04259 0.0054 0.1842 1.0000
17.000 1.5784 0.04995 0.04460 0.0059 0.1817 1.0000
17.250 1.5807 0.05204 0.04676 0.0064 0.1789 1.0000
17.500 1.5804 0.05441 0.04916 0.0069 0.1760 1.0000
17.750 1.5793 0.05689 0.05168 0.0073 0.1727 1.0000
18.000 1.5815 0.05922 0.05414 0.0074 0.1700 1.0000
18.250 1.5813 0.06183 0.05684 0.0074 0.1665 1.0000
18.500 1.5775 0.06485 0.05990 0.0074 0.1630 1.0000
18.750 1.5716 0.06808 0.06315 0.0074 0.1598 1.0000
19.000 1.5714 0.07076 0.06597 0.0072 0.1566 1.0000
19.250 1.5650 0.07421 0.06949 0.0069 0.1520 1.0000
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Polar data table (+)
Polar graphs
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