GOE 770 AIRFOIL (goe770-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 770 AIRFOIL (goe770-il) Reynolds number: 50,000 Max Cl/Cd: 2.92 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe770-il-50000.txt Download as CSV file: xf-goe770-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 770 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2480 0.12938 0.12346 -0.0237 0.9970 0.3397
-10.750 -0.2622 0.12711 0.12121 -0.0289 0.9868 0.3480
-10.500 -0.4929 0.08643 0.08043 -0.0585 0.9820 0.1839
-10.250 -0.5089 0.07841 0.07228 -0.0649 0.9705 0.1814
-10.000 -0.5498 0.07151 0.06519 -0.0680 0.9569 0.1785
-9.750 -0.5885 0.06540 0.05872 -0.0688 0.9435 0.1762
-9.500 -0.6020 0.06066 0.05357 -0.0695 0.9328 0.1763
-9.250 -0.6126 0.05769 0.05026 -0.0677 0.9212 0.1773
-9.000 -0.6037 0.05400 0.04607 -0.0688 0.9134 0.1798
-8.750 -0.6119 0.05218 0.04390 -0.0654 0.9028 0.1812
-8.500 -0.5907 0.04942 0.04074 -0.0665 0.8954 0.1852
-8.250 -0.5704 0.04834 0.03970 -0.0661 0.8869 0.1906
-8.000 -0.5572 0.04688 0.03794 -0.0650 0.8786 0.1960
-7.750 -0.5168 0.04504 0.03598 -0.0677 0.8729 0.2051
-7.500 -0.5215 0.04484 0.03569 -0.0635 0.8641 0.2097
-7.250 -0.4972 0.04372 0.03444 -0.0636 0.8569 0.2192
-7.000 -0.4564 0.04250 0.03311 -0.0659 0.8513 0.2349
-6.750 -0.4663 0.04280 0.03350 -0.0608 0.8433 0.2403
-6.500 -0.4460 0.04222 0.03292 -0.0601 0.8367 0.2558
-6.250 -0.4050 0.04114 0.03187 -0.0622 0.8311 0.2844
-6.000 -0.4149 0.04135 0.03221 -0.0572 0.8242 0.2964
-5.750 -0.4071 0.04091 0.03192 -0.0547 0.8180 0.3250
-5.500 -0.3807 0.04021 0.03201 -0.0538 0.8123 0.3905
-5.250 -0.3728 0.04124 0.03351 -0.0495 0.8066 0.4555
-5.000 -0.3819 0.04240 0.03481 -0.0437 0.8005 0.4914
-4.750 -0.3692 0.04378 0.03627 -0.0401 0.7945 0.5350
-4.500 -0.3243 0.04532 0.03777 -0.0396 0.7881 0.5831
-4.250 -0.3413 0.04628 0.03878 -0.0335 0.7827 0.5976
-4.000 -0.3375 0.04726 0.03977 -0.0296 0.7773 0.6209
-3.750 -0.3182 0.04815 0.04060 -0.0272 0.7712 0.6495
-3.500 -0.2922 0.04930 0.04170 -0.0250 0.7648 0.6780
-3.250 -0.3012 0.05017 0.04258 -0.0201 0.7604 0.6986
-3.000 -0.2967 0.05126 0.04369 -0.0158 0.7556 0.7220
-2.750 -0.2720 0.05262 0.04503 -0.0127 0.7490 0.7498
-2.500 -0.2483 0.05395 0.04628 -0.0101 0.7428 0.7774
-2.250 -0.2526 0.05483 0.04715 -0.0061 0.7397 0.7980
-2.000 -0.2470 0.05577 0.04806 -0.0033 0.7361 0.8195
-1.750 -0.2294 0.05681 0.04902 -0.0023 0.7319 0.8406
-1.500 -0.1671 0.05822 0.05020 -0.0068 0.7217 0.8612
-1.250 -0.1620 0.05930 0.05124 -0.0059 0.7203 0.8780
-1.000 -0.1508 0.06050 0.05238 -0.0060 0.7192 0.8948
-0.750 -0.1255 0.06221 0.05401 -0.0087 0.7192 0.9103
-0.500 -0.0199 0.06442 0.05595 -0.0214 0.7025 0.9227
-0.250 0.0116 0.06650 0.05796 -0.0258 0.7024 0.9361
0.750 0.0001 0.07654 0.06823 -0.0369 0.8148 0.9924
1.000 0.0325 0.07840 0.06999 -0.0415 0.8040 1.0000
1.500 0.0232 0.07813 0.06952 -0.0366 0.7854 1.0000
1.750 0.0040 0.07638 0.06768 -0.0316 0.7715 1.0000
2.000 0.0159 0.07800 0.06909 -0.0315 0.7662 1.0000
2.250 0.0043 0.07653 0.06749 -0.0278 0.7507 1.0000
2.500 0.0464 0.08044 0.07118 -0.0319 0.7453 1.0000
2.750 0.0331 0.07912 0.06975 -0.0282 0.7311 1.0000
3.000 0.0682 0.08220 0.07265 -0.0310 0.7252 1.0000
3.250 0.0644 0.08244 0.07280 -0.0288 0.7158 1.0000
3.500 0.0885 0.08440 0.07462 -0.0299 0.7066 1.0000
3.750 0.1315 0.08886 0.07892 -0.0335 0.7022 1.0000
4.000 0.1138 0.08742 0.07743 -0.0295 0.6894 1.0000
4.250 0.1451 0.09031 0.08021 -0.0314 0.6831 1.0000
4.500 0.1736 0.09403 0.08381 -0.0334 0.6797 1.0000
4.750 0.1601 0.09284 0.08260 -0.0300 0.6675 1.0000
5.000 0.1907 0.09586 0.08552 -0.0318 0.6616 1.0000
5.250 0.2108 0.09893 0.08850 -0.0327 0.6575 1.0000
5.500 0.2051 0.09849 0.08803 -0.0305 0.6456 1.0000
5.750 0.2333 0.10149 0.09097 -0.0320 0.6403 1.0000
6.000 0.2743 0.10682 0.09622 -0.0351 0.6374 1.0000
6.250 0.2456 0.10432 0.09371 -0.0307 0.6260 1.0000
6.500 0.2716 0.10712 0.09647 -0.0319 0.6196 1.0000
6.750 0.3111 0.11229 0.10158 -0.0347 0.6163 1.0000
7.000 0.2859 0.11048 0.09977 -0.0312 0.6068 1.0000
7.250 0.3068 0.11290 0.10216 -0.0319 0.5996 1.0000
7.500 0.3434 0.11765 0.10688 -0.0342 0.5956 1.0000
7.750 0.3260 0.11697 0.10620 -0.0318 0.5877 1.0000
8.000 0.3423 0.11906 0.10828 -0.0322 0.5797 1.0000
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Polar data table (+)
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