GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 377 AIRFOIL (goe377-il) Reynolds number: 500,000 Max Cl/Cd: 101.47 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe377-il-500000.txt Download as CSV file: xf-goe377-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 377 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3764 0.08542 0.08330 -0.0226 1.0000 0.0156
-7.250 -0.3873 0.08362 0.08156 -0.0206 1.0000 0.0160
-7.000 -0.3944 0.08155 0.07953 -0.0195 1.0000 0.0162
-6.750 -0.4025 0.07949 0.07752 -0.0186 1.0000 0.0168
-6.500 -0.3777 0.07486 0.07285 -0.0280 0.9974 0.0175
-6.250 -0.3411 0.06935 0.06726 -0.0376 0.9939 0.0177
-6.000 -0.3102 0.06413 0.06195 -0.0444 0.9896 0.0178
-4.000 -0.0398 0.01006 0.00660 -0.0765 0.9561 0.0240
-3.750 -0.0378 0.02179 0.01774 -0.0754 0.9579 0.0224
-3.500 -0.0094 0.01819 0.01364 -0.0752 0.9535 0.0235
-3.000 0.0484 0.01348 0.00812 -0.0752 0.9442 0.0276
-2.750 0.0774 0.01295 0.00751 -0.0753 0.9388 0.0301
-2.500 0.1069 0.01253 0.00697 -0.0754 0.9325 0.0339
-2.250 0.1369 0.01209 0.00637 -0.0754 0.9255 0.0358
-2.000 0.1636 0.01059 0.00474 -0.0751 0.9157 0.0397
-1.750 0.1897 0.01018 0.00426 -0.0744 0.9036 0.0424
-1.500 0.2158 0.00970 0.00371 -0.0737 0.8920 0.0443
-1.250 0.2422 0.00942 0.00335 -0.0731 0.8811 0.0469
-1.000 0.2686 0.00919 0.00306 -0.0725 0.8703 0.0482
-0.750 0.2928 0.00859 0.00240 -0.0716 0.8587 0.0505
-0.500 0.3177 0.00830 0.00209 -0.0707 0.8461 0.0532
-0.250 0.3432 0.00812 0.00187 -0.0700 0.8330 0.0565
0.000 0.3688 0.00800 0.00170 -0.0694 0.8186 0.0615
0.250 0.3939 0.00781 0.00148 -0.0686 0.8028 0.0747
0.750 0.5124 0.00557 0.00149 -0.0832 0.7679 1.0000
1.000 0.5359 0.00567 0.00145 -0.0821 0.7458 1.0000
1.250 0.5593 0.00578 0.00144 -0.0810 0.7219 1.0000
1.500 0.5825 0.00592 0.00144 -0.0799 0.6972 1.0000
1.750 0.6054 0.00608 0.00147 -0.0788 0.6709 1.0000
2.000 0.6281 0.00625 0.00151 -0.0776 0.6430 1.0000
2.250 0.6509 0.00644 0.00157 -0.0764 0.6162 1.0000
2.500 0.6736 0.00664 0.00166 -0.0753 0.5891 1.0000
2.750 0.6961 0.00686 0.00175 -0.0742 0.5614 1.0000
3.000 0.7185 0.00710 0.00186 -0.0730 0.5316 1.0000
3.250 0.7408 0.00735 0.00198 -0.0719 0.5007 1.0000
3.500 0.7628 0.00763 0.00213 -0.0707 0.4666 1.0000
3.750 0.7854 0.00789 0.00228 -0.0696 0.4371 1.0000
4.000 0.8078 0.00817 0.00245 -0.0686 0.4067 1.0000
4.250 0.8299 0.00848 0.00264 -0.0675 0.3759 1.0000
4.500 0.8513 0.00886 0.00286 -0.0663 0.3420 1.0000
4.750 0.8729 0.00924 0.00312 -0.0651 0.3123 1.0000
5.000 0.8954 0.00954 0.00335 -0.0642 0.2903 1.0000
5.250 0.9180 0.00985 0.00359 -0.0632 0.2706 1.0000
5.500 0.9404 0.01017 0.00384 -0.0623 0.2474 1.0000
5.750 0.9620 0.01056 0.00413 -0.0612 0.2177 1.0000
6.000 0.9828 0.01104 0.00445 -0.0600 0.1799 1.0000
6.250 0.9966 0.01219 0.00510 -0.0578 0.0939 1.0000
6.500 1.0089 0.01359 0.00607 -0.0552 0.0239 1.0000
6.750 1.0289 0.01421 0.00671 -0.0537 0.0191 1.0000
7.000 1.0474 0.01500 0.00763 -0.0519 0.0167 1.0000
7.250 1.0669 0.01564 0.00841 -0.0504 0.0160 1.0000
7.500 1.0848 0.01642 0.00929 -0.0486 0.0150 1.0000
7.750 1.1017 0.01725 0.01022 -0.0467 0.0142 1.0000
8.000 1.1178 0.01812 0.01116 -0.0448 0.0129 1.0000
8.250 1.1312 0.01924 0.01236 -0.0424 0.0122 1.0000
8.500 1.1412 0.02071 0.01394 -0.0395 0.0117 1.0000
8.750 1.1493 0.02269 0.01604 -0.0365 0.0113 1.0000
9.000 1.1606 0.02524 0.01876 -0.0340 0.0111 1.0000
9.250 1.1773 0.02596 0.01961 -0.0322 0.0106 1.0000
9.500 1.1922 0.02813 0.02194 -0.0305 0.0107 1.0000
9.750 1.2064 0.03029 0.02430 -0.0286 0.0106 1.0000
10.000 1.2180 0.03390 0.02818 -0.0266 0.0108 1.0000
10.250 1.2315 0.03755 0.03201 -0.0252 0.0112 1.0000
10.500 1.2363 0.04046 0.03519 -0.0225 0.0112 1.0000
10.750 1.2435 0.04184 0.03672 -0.0200 0.0113 1.0000
11.000 1.2455 0.04336 0.03842 -0.0167 0.0114 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 377 AIRFOIL (goe377-il)