GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 802 B AIRFOIL (goe802b-il) Reynolds number: 500,000 Max Cl/Cd: 104.6 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe802b-il-500000.txt Download as CSV file: xf-goe802b-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 B 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3096 0.11217 0.10988 -0.0258 1.0000 0.0207
-9.750 -0.3062 0.10918 0.10691 -0.0288 1.0000 0.0207
-9.500 -0.3033 0.10613 0.10387 -0.0318 1.0000 0.0208
-9.250 -0.2984 0.10246 0.10023 -0.0331 1.0000 0.0209
-9.000 -0.2890 0.09883 0.09662 -0.0322 1.0000 0.0210
-8.750 -0.2838 0.09617 0.09399 -0.0321 1.0000 0.0212
-8.500 -0.2810 0.09387 0.09173 -0.0321 0.9984 0.0213
-8.250 -0.2629 0.09026 0.08812 -0.0363 0.9941 0.0217
-8.000 -0.2456 0.08676 0.08461 -0.0407 0.9868 0.0222
-7.750 -0.2271 0.08303 0.08088 -0.0459 0.9789 0.0229
-7.500 -0.2095 0.07926 0.07710 -0.0512 0.9684 0.0237
-7.250 -0.1876 0.07505 0.07283 -0.0602 0.9545 0.0248
-7.000 -0.1648 0.07063 0.06831 -0.0697 0.9415 0.0249
-6.750 -0.1451 0.06674 0.06429 -0.0745 0.9317 0.0250
-6.500 -0.1361 0.06297 0.06054 -0.0740 0.9225 0.0252
-6.250 -0.1243 0.06033 0.05786 -0.0735 0.9144 0.0254
-6.000 -0.1078 0.05768 0.05519 -0.0747 0.9054 0.0257
-5.750 -0.0891 0.05500 0.05242 -0.0765 0.8974 0.0261
-5.500 -0.0674 0.05216 0.04951 -0.0788 0.8888 0.0267
-5.250 -0.0447 0.04929 0.04653 -0.0810 0.8801 0.0275
-5.000 -0.0180 0.04623 0.04333 -0.0836 0.8707 0.0289
-4.750 0.0221 0.04314 0.03973 -0.0877 0.8616 0.0298
-4.500 0.0393 0.03923 0.03585 -0.0884 0.8526 0.0302
-4.250 0.0604 0.03708 0.03363 -0.0888 0.8441 0.0305
-4.000 0.0840 0.03511 0.03159 -0.0895 0.8354 0.0310
-3.750 0.1088 0.03329 0.02963 -0.0900 0.8261 0.0319
-3.500 0.1356 0.03141 0.02759 -0.0906 0.8165 0.0334
-3.250 0.1691 0.02996 0.02560 -0.0907 0.8073 0.0354
-3.000 0.1924 0.02736 0.02300 -0.0913 0.7973 0.0359
-2.750 0.2173 0.02580 0.02134 -0.0915 0.7877 0.0366
-2.500 0.2439 0.02449 0.01992 -0.0918 0.7765 0.0378
-2.250 0.2759 0.02515 0.02012 -0.0910 0.7656 0.0412
-2.000 0.3005 0.02223 0.01714 -0.0916 0.7538 0.0420
-1.750 0.3266 0.02092 0.01577 -0.0919 0.7404 0.0430
-1.500 0.3537 0.02010 0.01480 -0.0919 0.7260 0.0453
-1.250 0.3826 0.01959 0.01398 -0.0915 0.7111 0.0483
-1.000 0.4091 0.01839 0.01269 -0.0917 0.6952 0.0494
-0.750 0.4364 0.01774 0.01190 -0.0916 0.6787 0.0519
-0.500 0.4650 0.01747 0.01134 -0.0912 0.6614 0.0549
-0.250 0.4917 0.01644 0.01021 -0.0913 0.6438 0.0563
0.000 0.5203 0.01716 0.01067 -0.0908 0.6265 0.0605
0.250 0.5477 0.01608 0.00943 -0.0908 0.6106 0.0611
0.500 0.5748 0.01508 0.00836 -0.0908 0.5956 0.0619
0.750 0.6022 0.01456 0.00774 -0.0908 0.5813 0.0633
1.000 0.6300 0.01177 0.00449 -0.0899 0.5701 0.0410
1.250 0.6558 0.01095 0.00363 -0.0897 0.5572 0.0415
1.500 0.6831 0.01083 0.00348 -0.0897 0.5444 0.0431
1.750 0.7104 0.01085 0.00347 -0.0895 0.5319 0.0451
2.000 0.7371 0.01083 0.00340 -0.0894 0.5187 0.0476
2.250 0.7650 0.01115 0.00368 -0.0893 0.5041 0.0510
2.500 0.7923 0.01136 0.00385 -0.0891 0.4893 0.0561
2.750 0.8198 0.01169 0.00409 -0.0890 0.4761 0.0672
3.000 0.8472 0.01208 0.00438 -0.0888 0.4631 0.0792
3.250 0.8741 0.01217 0.00440 -0.0888 0.4503 0.0919
3.500 0.9007 0.01206 0.00428 -0.0887 0.4377 0.0974
3.750 0.9270 0.01201 0.00422 -0.0886 0.4257 0.1032
4.000 0.9533 0.01200 0.00419 -0.0884 0.4141 0.1089
4.250 0.9799 0.01206 0.00425 -0.0883 0.4042 0.1115
4.500 1.0058 0.01220 0.00434 -0.0881 0.3940 0.1154
4.750 1.0323 0.01198 0.00423 -0.0881 0.3835 0.1220
5.000 1.0583 0.01199 0.00425 -0.0880 0.3729 0.1271
5.250 1.0844 0.01206 0.00433 -0.0879 0.3629 0.1307
5.500 1.1106 0.01217 0.00443 -0.0878 0.3542 0.1339
5.750 1.1365 0.01233 0.00459 -0.0876 0.3455 0.1373
6.000 1.1623 0.01247 0.00480 -0.0875 0.3375 0.1833
6.250 1.1877 0.01266 0.00503 -0.0873 0.3274 0.2093
6.500 1.2112 0.01191 0.00543 -0.0871 0.3181 0.7830
6.750 1.2340 0.01181 0.00565 -0.0861 0.3087 1.0000
7.000 1.2594 0.01204 0.00589 -0.0858 0.2994 1.0000
7.250 1.2836 0.01235 0.00615 -0.0854 0.2868 1.0000
7.500 1.3074 0.01269 0.00644 -0.0850 0.2706 1.0000
7.750 1.3308 0.01306 0.00674 -0.0845 0.2508 1.0000
8.000 1.3531 0.01352 0.00709 -0.0838 0.2283 1.0000
8.250 1.3738 0.01411 0.00753 -0.0830 0.2049 1.0000
8.500 1.3942 0.01470 0.00803 -0.0821 0.1859 1.0000
8.750 1.4143 0.01529 0.00855 -0.0811 0.1713 1.0000
9.250 1.4543 0.01639 0.00957 -0.0792 0.1491 1.0000
9.500 1.4737 0.01695 0.01011 -0.0781 0.1406 1.0000
9.750 1.4931 0.01747 0.01063 -0.0771 0.1320 1.0000
10.000 1.5116 0.01803 0.01119 -0.0759 0.1239 1.0000
10.250 1.5282 0.01866 0.01178 -0.0744 0.1141 1.0000
10.500 1.5438 0.01925 0.01237 -0.0728 0.1044 1.0000
10.750 1.5563 0.01998 0.01306 -0.0707 0.0935 1.0000
11.000 1.5671 0.02085 0.01387 -0.0685 0.0816 1.0000
11.250 1.5761 0.02187 0.01482 -0.0663 0.0706 1.0000
11.500 1.5844 0.02298 0.01589 -0.0641 0.0626 1.0000
11.750 1.5944 0.02402 0.01694 -0.0622 0.0560 1.0000
12.000 1.6026 0.02522 0.01816 -0.0603 0.0490 1.0000
12.250 1.6068 0.02679 0.01968 -0.0582 0.0361 1.0000
12.500 1.5991 0.02939 0.02215 -0.0554 0.0220 1.0000
12.750 1.6009 0.03136 0.02418 -0.0536 0.0197 1.0000
13.000 1.6052 0.03320 0.02613 -0.0521 0.0187 1.0000
13.250 1.6084 0.03523 0.02827 -0.0509 0.0180 1.0000
13.500 1.6096 0.03751 0.03068 -0.0497 0.0174 1.0000
13.750 1.6089 0.04010 0.03339 -0.0487 0.0169 1.0000
14.000 1.6060 0.04303 0.03644 -0.0479 0.0165 1.0000
14.250 1.6006 0.04638 0.03992 -0.0473 0.0161 1.0000
14.500 1.5932 0.05013 0.04380 -0.0470 0.0158 1.0000
14.750 1.5830 0.05440 0.04821 -0.0471 0.0155 1.0000
15.000 1.5759 0.05847 0.05241 -0.0474 0.0153 1.0000
15.250 1.5694 0.06259 0.05666 -0.0480 0.0152 1.0000
15.500 1.5610 0.06707 0.06127 -0.0487 0.0150 1.0000
15.750 1.5515 0.07180 0.06613 -0.0496 0.0149 1.0000
16.000 1.5408 0.07683 0.07130 -0.0507 0.0147 1.0000
16.250 1.5291 0.08206 0.07665 -0.0520 0.0146 1.0000
16.500 1.5169 0.08745 0.08217 -0.0534 0.0144 1.0000
16.750 1.5048 0.09292 0.08776 -0.0550 0.0143 1.0000
17.000 1.4921 0.09856 0.09352 -0.0566 0.0141 1.0000
17.250 1.4796 0.10423 0.09931 -0.0584 0.0140 1.0000
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