GOE 269 AIRFOIL (goe269-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 269 AIRFOIL (goe269-il) Reynolds number: 500,000 Max Cl/Cd: 107.75 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe269-il-500000.txt Download as CSV file: xf-goe269-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 269 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3571 0.09878 0.09654 -0.0113 1.0000 0.0240
-8.000 -0.3510 0.09565 0.09343 -0.0137 1.0000 0.0254
-7.750 -0.3496 0.09285 0.09066 -0.0186 1.0000 0.0258
-7.500 -0.3392 0.08905 0.08689 -0.0251 1.0000 0.0259
-7.250 -0.3313 0.08437 0.08223 -0.0272 1.0000 0.0261
-7.000 -0.3227 0.08159 0.07946 -0.0250 1.0000 0.0265
-6.750 -0.3135 0.07932 0.07722 -0.0250 1.0000 0.0269
-6.500 -0.3077 0.07727 0.07520 -0.0251 1.0000 0.0275
-6.250 -0.2812 0.07358 0.07150 -0.0310 0.9958 0.0287
-6.000 -0.2210 0.06678 0.06456 -0.0514 0.9874 0.0315
-5.750 -0.1919 0.06054 0.05827 -0.0583 0.9793 0.0320
-5.250 -0.1406 0.05522 0.05290 -0.0628 0.9566 0.0335
-5.000 -0.1108 0.05216 0.04976 -0.0669 0.9405 0.0349
-4.750 -0.0559 0.04741 0.04469 -0.0781 0.9237 0.0382
-4.500 -0.0349 0.04240 0.03955 -0.0807 0.9080 0.0390
-4.250 -0.0151 0.04066 0.03774 -0.0806 0.8912 0.0396
-4.000 0.0088 0.03881 0.03579 -0.0813 0.8752 0.0405
-3.750 0.0361 0.03673 0.03358 -0.0828 0.8598 0.0419
-3.500 0.0812 0.03428 0.03073 -0.0865 0.8451 0.0462
-3.250 0.1097 0.02943 0.02563 -0.0892 0.8298 0.0472
-3.000 0.1346 0.02792 0.02404 -0.0897 0.8123 0.0479
-2.750 0.1613 0.02657 0.02255 -0.0902 0.7950 0.0489
-2.500 0.1896 0.02517 0.02098 -0.0908 0.7786 0.0505
-2.250 0.2253 0.02450 0.01990 -0.0910 0.7637 0.0556
-2.000 0.2607 0.01749 0.01221 -0.0938 0.7527 0.0477
-1.750 0.2916 0.01519 0.00952 -0.0943 0.7407 0.0450
-1.500 0.3220 0.01337 0.00730 -0.0947 0.7290 0.0453
-1.250 0.3513 0.01243 0.00610 -0.0948 0.7181 0.0461
-1.000 0.3802 0.01141 0.00487 -0.0950 0.7083 0.0478
-0.750 0.4085 0.01131 0.00473 -0.0949 0.6980 0.0496
-0.500 0.4371 0.01103 0.00437 -0.0949 0.6880 0.0514
-0.250 0.4656 0.01076 0.00400 -0.0948 0.6790 0.0537
0.000 0.4941 0.01065 0.00381 -0.0947 0.6693 0.0558
0.250 0.5226 0.01022 0.00338 -0.0948 0.6599 0.0596
0.500 0.5508 0.01023 0.00334 -0.0947 0.6500 0.0639
0.750 0.5793 0.01004 0.00313 -0.0947 0.6401 0.0689
1.000 0.6075 0.00995 0.00304 -0.0947 0.6301 0.0738
1.250 0.6356 0.00994 0.00299 -0.0946 0.6190 0.0783
1.500 0.6640 0.00972 0.00278 -0.0946 0.6064 0.0836
1.750 0.6921 0.00969 0.00274 -0.0945 0.5917 0.0886
2.000 0.7200 0.00970 0.00271 -0.0944 0.5746 0.0924
2.250 0.7481 0.00960 0.00257 -0.0944 0.5559 0.0971
2.500 0.7761 0.00961 0.00256 -0.0944 0.5336 0.1018
2.750 0.8037 0.00970 0.00255 -0.0943 0.5079 0.1055
3.000 0.8310 0.00983 0.00257 -0.0941 0.4803 0.1103
3.250 0.8584 0.00997 0.00267 -0.0940 0.4575 0.1185
3.500 0.8859 0.01011 0.00279 -0.0940 0.4411 0.1382
3.750 0.9075 0.00871 0.00301 -0.0930 0.4287 1.0000
4.000 0.9349 0.00894 0.00314 -0.0928 0.4166 1.0000
4.500 0.9896 0.00936 0.00347 -0.0926 0.3945 1.0000
4.750 1.0168 0.00957 0.00364 -0.0924 0.3841 1.0000
5.000 1.0438 0.00980 0.00384 -0.0923 0.3728 1.0000
5.250 1.0710 0.01000 0.00403 -0.0922 0.3616 1.0000
5.500 1.0981 0.01021 0.00422 -0.0920 0.3497 1.0000
5.750 1.1249 0.01044 0.00442 -0.0919 0.3347 1.0000
6.000 1.1513 0.01071 0.00465 -0.0917 0.3174 1.0000
6.250 1.1775 0.01102 0.00489 -0.0914 0.2967 1.0000
6.500 1.2030 0.01141 0.00516 -0.0911 0.2684 1.0000
6.750 1.2276 0.01192 0.00552 -0.0908 0.2317 1.0000
7.000 1.2510 0.01262 0.00599 -0.0903 0.1919 1.0000
7.250 1.2743 0.01329 0.00650 -0.0898 0.1649 1.0000
7.500 1.2982 0.01385 0.00699 -0.0893 0.1477 1.0000
7.750 1.3223 0.01435 0.00747 -0.0888 0.1359 1.0000
8.000 1.3460 0.01488 0.00795 -0.0883 0.1252 1.0000
8.250 1.3700 0.01534 0.00840 -0.0879 0.1149 1.0000
8.500 1.3940 0.01579 0.00886 -0.0874 0.1048 1.0000
8.750 1.4172 0.01630 0.00935 -0.0868 0.0918 1.0000
9.000 1.4383 0.01705 0.00996 -0.0860 0.0680 1.0000
9.250 1.4532 0.01853 0.01113 -0.0844 0.0334 1.0000
9.500 1.4710 0.01959 0.01215 -0.0831 0.0247 1.0000
9.750 1.4883 0.02064 0.01323 -0.0816 0.0213 1.0000
10.000 1.5070 0.02145 0.01414 -0.0804 0.0198 1.0000
10.250 1.5235 0.02241 0.01518 -0.0789 0.0185 1.0000
10.500 1.5359 0.02369 0.01653 -0.0769 0.0173 1.0000
10.750 1.5457 0.02505 0.01801 -0.0745 0.0166 1.0000
11.000 1.5571 0.02611 0.01918 -0.0724 0.0161 1.0000
11.250 1.5637 0.02729 0.02046 -0.0695 0.0157 1.0000
11.500 1.5677 0.02863 0.02192 -0.0665 0.0152 1.0000
11.750 1.5711 0.03016 0.02356 -0.0640 0.0148 1.0000
12.000 1.5734 0.03195 0.02543 -0.0617 0.0143 1.0000
12.250 1.5738 0.03406 0.02764 -0.0598 0.0139 1.0000
12.500 1.5706 0.03669 0.03037 -0.0581 0.0136 1.0000
12.750 1.5628 0.04001 0.03382 -0.0566 0.0132 1.0000
13.000 1.5542 0.04366 0.03759 -0.0555 0.0130 1.0000
13.250 1.5563 0.04627 0.04033 -0.0550 0.0128 1.0000
13.500 1.5566 0.04919 0.04338 -0.0547 0.0126 1.0000
13.750 1.5550 0.05237 0.04671 -0.0545 0.0125 1.0000
14.000 1.5524 0.05577 0.05023 -0.0544 0.0123 1.0000
14.250 1.5488 0.05935 0.05394 -0.0545 0.0121 1.0000
14.500 1.5441 0.06310 0.05781 -0.0547 0.0120 1.0000
14.750 1.5387 0.06701 0.06186 -0.0551 0.0118 1.0000
15.000 1.5327 0.07109 0.06606 -0.0556 0.0117 1.0000
15.250 1.5264 0.07533 0.07042 -0.0563 0.0115 1.0000
15.500 1.5200 0.07973 0.07495 -0.0572 0.0114 1.0000
15.750 1.5130 0.08433 0.07967 -0.0583 0.0113 1.0000
16.000 1.5055 0.08912 0.08458 -0.0596 0.0112 1.0000
16.250 1.4977 0.09408 0.08968 -0.0611 0.0111 1.0000
16.500 1.4895 0.09922 0.09494 -0.0629 0.0110 1.0000
16.750 1.4811 0.10449 0.10033 -0.0648 0.0109 1.0000
17.000 1.4723 0.10991 0.10587 -0.0669 0.0108 1.0000
17.250 1.4633 0.11548 0.11158 -0.0693 0.0107 1.0000
17.500 1.4544 0.12115 0.11737 -0.0719 0.0106 1.0000
17.750 1.4456 0.12690 0.12323 -0.0746 0.0105 1.0000
18.000 1.4361 0.13286 0.12931 -0.0776 0.0105 1.0000
18.250 1.4271 0.13880 0.13536 -0.0807 0.0104 1.0000
18.500 1.4172 0.14516 0.14184 -0.0843 0.0103 1.0000
18.750 1.4066 0.15187 0.14867 -0.0882 0.0102 1.0000
19.000 1.3958 0.15887 0.15580 -0.0926 0.0102 1.0000
19.250 1.3843 0.16634 0.16341 -0.0974 0.0102 1.0000
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