GOE 780 AIRFOIL (goe780-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 780 AIRFOIL (goe780-il) Reynolds number: 100,000 Max Cl/Cd: 29.32 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe780-il-100000.txt Download as CSV file: xf-goe780-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 780 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3764 0.10821 0.10372 -0.0472 1.0000 0.0915
-11.000 -0.3969 0.10458 0.10018 -0.0508 1.0000 0.0931
-10.750 -0.4759 0.10639 0.10161 -0.0466 1.0000 0.0849
-10.500 -0.4766 0.10290 0.09817 -0.0474 1.0000 0.0884
-10.250 -0.4901 0.09867 0.09403 -0.0509 1.0000 0.0918
-10.000 -0.5081 0.09396 0.08941 -0.0554 1.0000 0.0926
-9.750 -0.5319 0.09017 0.08566 -0.0575 1.0000 0.0929
-9.500 -0.5559 0.08759 0.08312 -0.0563 1.0000 0.0931
-9.250 -0.5821 0.08602 0.08162 -0.0524 1.0000 0.0932
-9.000 -0.6111 0.08545 0.08114 -0.0458 1.0000 0.0931
-8.750 -0.6367 0.08487 0.08063 -0.0392 1.0000 0.0929
-8.500 -0.6645 0.08414 0.07992 -0.0330 1.0000 0.0929
-8.250 -0.6941 0.08338 0.07911 -0.0269 1.0000 0.0931
-8.000 -0.7222 0.08261 0.07821 -0.0210 1.0000 0.0934
-7.750 -0.7480 0.08201 0.07741 -0.0150 1.0000 0.0937
-7.500 -0.7223 0.07435 0.07013 -0.0161 1.0000 0.0988
-7.250 -0.7344 0.07228 0.06798 -0.0120 1.0000 0.1014
-7.000 -0.7635 0.07285 0.06797 -0.0059 0.9977 0.1070
-6.750 -0.7453 0.06612 0.06151 -0.0068 0.9958 0.1122
-4.750 -0.6626 0.04272 0.03461 0.0132 0.9681 0.0937
-4.500 -0.6339 0.03722 0.02852 0.0154 0.9664 0.0672
-4.250 -0.6093 0.03420 0.02518 0.0165 0.9641 0.0620
-4.000 -0.5786 0.03190 0.02225 0.0174 0.9616 0.0579
-3.750 -0.5473 0.03024 0.02044 0.0166 0.9591 0.0644
-3.500 -0.5076 0.02855 0.01846 0.0149 0.9571 0.0672
-3.250 -0.4699 0.02678 0.01677 0.0131 0.9555 0.0736
-3.000 -0.4564 0.02603 0.01595 0.0157 0.9525 0.0830
-2.750 -0.0430 0.02682 0.01933 -0.0499 0.9754 1.0000
-2.500 -0.0161 0.02666 0.01902 -0.0515 0.9716 1.0000
-2.250 0.0120 0.02656 0.01874 -0.0532 0.9682 1.0000
-2.000 0.0262 0.02650 0.01858 -0.0521 0.9631 1.0000
-1.750 0.0484 0.02648 0.01846 -0.0525 0.9593 1.0000
-1.500 0.0782 0.02647 0.01836 -0.0544 0.9561 1.0000
-1.250 0.0882 0.02657 0.01841 -0.0523 0.9513 1.0000
-1.000 0.1047 0.02668 0.01845 -0.0515 0.9471 1.0000
-0.750 0.1307 0.02678 0.01849 -0.0525 0.9437 1.0000
-0.500 0.1480 0.02698 0.01865 -0.0518 0.9401 1.0000
-0.250 0.1554 0.02722 0.01888 -0.0491 0.9353 1.0000
0.000 0.1755 0.02744 0.01908 -0.0489 0.9316 1.0000
0.250 0.2023 0.02769 0.01934 -0.0498 0.9289 1.0000
0.500 0.2037 0.02806 0.01971 -0.0459 0.9240 1.0000
0.750 0.2156 0.02841 0.02007 -0.0441 0.9201 1.0000
1.000 0.2376 0.02874 0.02043 -0.0441 0.9168 1.0000
1.250 0.2571 0.02914 0.02088 -0.0436 0.9135 1.0000
1.500 0.2558 0.02962 0.02138 -0.0392 0.9090 1.0000
1.750 0.2717 0.03003 0.02188 -0.0381 0.9051 1.0000
2.000 0.2942 0.03050 0.02244 -0.0381 0.9023 1.0000
2.250 0.2995 0.03101 0.02301 -0.0350 0.8976 1.0000
2.500 0.3535 0.03097 0.02316 -0.0401 0.8869 1.0000
2.750 0.5797 0.01977 0.00938 -0.0549 0.1136 1.0000
3.000 0.5844 0.02112 0.01065 -0.0502 0.0776 1.0000
3.250 0.5932 0.02200 0.01161 -0.0467 0.0678 1.0000
3.500 0.6010 0.02297 0.01259 -0.0431 0.0592 1.0000
3.750 0.6121 0.02396 0.01363 -0.0398 0.0559 1.0000
4.000 0.6293 0.02513 0.01480 -0.0375 0.0541 1.0000
4.250 0.6558 0.02660 0.01628 -0.0367 0.0531 1.0000
4.500 0.6890 0.02848 0.01827 -0.0368 0.0537 1.0000
4.750 0.7202 0.03048 0.02046 -0.0365 0.0541 1.0000
5.000 0.7447 0.03220 0.02244 -0.0352 0.0520 1.0000
5.250 0.7730 0.03524 0.02579 -0.0344 0.0565 1.0000
8.750 0.8806 0.08120 0.07551 0.0104 0.0988 1.0000
9.000 0.8534 0.08134 0.07595 0.0172 0.0984 1.0000
9.250 0.8242 0.08206 0.07687 0.0236 0.0980 1.0000
9.500 0.7972 0.08361 0.07853 0.0293 0.0976 1.0000
9.750 0.7671 0.08503 0.08001 0.0351 0.0973 1.0000
10.000 0.7385 0.08714 0.08217 0.0391 0.0970 1.0000
10.250 0.7200 0.09035 0.08540 0.0410 0.0972 1.0000
10.500 0.6928 0.09386 0.08894 0.0418 0.0970 1.0000
10.750 0.6654 0.09837 0.09346 0.0408 0.0966 1.0000
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