GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 795 smoothed (goe795sm-il) Reynolds number: 100,000 Max Cl/Cd: 56.52 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe795sm-il-100000.txt Download as CSV file: xf-goe795sm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 smoothed
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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3544 0.10737 0.10246 -0.0270 1.0000 0.0860
-9.750 -0.3665 0.10496 0.10011 -0.0296 1.0000 0.0875
-9.500 -0.3822 0.10256 0.09780 -0.0326 1.0000 0.0880
-9.250 -0.3559 0.09643 0.09164 -0.0286 1.0000 0.0914
-9.000 -0.3504 0.09320 0.08844 -0.0281 1.0000 0.0956
-8.750 -0.3592 0.09021 0.08551 -0.0296 1.0000 0.1001
-8.500 -0.3765 0.08747 0.08286 -0.0322 1.0000 0.1014
-8.250 -0.3918 0.08453 0.08003 -0.0340 1.0000 0.1018
-8.000 -0.3597 0.07949 0.07493 -0.0290 1.0000 0.1098
-7.750 -0.3706 0.07647 0.07200 -0.0298 1.0000 0.1133
-7.500 -0.3951 0.07402 0.06968 -0.0310 1.0000 0.1148
-7.250 -0.4611 0.08040 0.07580 -0.0285 1.0000 0.1069
-7.000 -0.4630 0.07743 0.07286 -0.0294 1.0000 0.1123
-6.750 -0.4808 0.07410 0.06937 -0.0371 1.0000 0.1157
-6.500 -0.4658 0.07050 0.06599 -0.0304 1.0000 0.1203
-6.250 -0.4772 0.06802 0.06317 -0.0360 1.0000 0.1298
-6.000 -0.4651 0.06376 0.05919 -0.0313 1.0000 0.1326
-5.750 -0.4586 0.06125 0.05666 -0.0294 1.0000 0.1383
-5.500 -0.4564 0.05782 0.05314 -0.0295 1.0000 0.1471
-5.250 -0.4519 0.05500 0.05016 -0.0295 1.0000 0.1591
-5.000 -0.4428 0.05249 0.04772 -0.0268 1.0000 0.1650
-4.750 -0.4253 0.03932 0.03302 -0.0310 1.0000 0.0895
-4.500 -0.4087 0.03425 0.02718 -0.0289 1.0000 0.0737
-4.250 -0.3937 0.03139 0.02376 -0.0270 1.0000 0.0750
-4.000 -0.3773 0.02871 0.02102 -0.0258 1.0000 0.0782
-3.750 -0.3577 0.02626 0.01804 -0.0240 1.0000 0.0782
-3.500 -0.3375 0.02471 0.01620 -0.0226 1.0000 0.0828
-3.250 -0.3166 0.02341 0.01437 -0.0210 1.0000 0.0890
-3.000 -0.2955 0.02185 0.01275 -0.0198 1.0000 0.0946
-2.750 -0.2747 0.02090 0.01155 -0.0185 1.0000 0.1039
-2.500 -0.2541 0.02004 0.01064 -0.0173 1.0000 0.1132
-2.250 -0.2338 0.01918 0.00982 -0.0160 1.0000 0.1237
-2.000 -0.2143 0.01865 0.00932 -0.0148 1.0000 0.1400
-1.750 -0.1950 0.01812 0.00884 -0.0134 1.0000 0.1582
-1.500 -0.1767 0.01767 0.00863 -0.0120 1.0000 0.1913
-1.250 -0.0882 0.01452 0.00830 -0.0234 1.0000 1.0000
-1.000 -0.0708 0.01482 0.00832 -0.0221 1.0000 1.0000
-0.750 -0.0357 0.01527 0.00849 -0.0244 0.9953 1.0000
-0.500 0.0098 0.01573 0.00867 -0.0286 0.9865 1.0000
-0.250 0.0542 0.01614 0.00889 -0.0326 0.9774 1.0000
0.000 0.1011 0.01655 0.00913 -0.0369 0.9688 1.0000
0.250 0.1444 0.01682 0.00926 -0.0404 0.9587 1.0000
0.500 0.1858 0.01703 0.00938 -0.0435 0.9478 1.0000
0.750 0.2285 0.01721 0.00949 -0.0467 0.9374 1.0000
1.000 0.2800 0.01730 0.00954 -0.0515 0.9293 1.0000
1.250 0.3187 0.01735 0.00957 -0.0538 0.9175 1.0000
1.500 0.3587 0.01737 0.00960 -0.0561 0.9060 1.0000
1.750 0.4022 0.01729 0.00956 -0.0591 0.8954 1.0000
2.000 0.4592 0.01696 0.00929 -0.0644 0.8882 1.0000
2.250 0.4997 0.01676 0.00919 -0.0664 0.8759 1.0000
2.500 0.5399 0.01653 0.00903 -0.0683 0.8634 1.0000
2.750 0.5798 0.01625 0.00885 -0.0699 0.8501 1.0000
3.000 0.6184 0.01594 0.00866 -0.0711 0.8355 1.0000
3.250 0.6555 0.01560 0.00842 -0.0718 0.8194 1.0000
3.500 0.6858 0.01535 0.00823 -0.0712 0.7987 1.0000
3.750 0.7176 0.01500 0.00793 -0.0705 0.7758 1.0000
4.000 0.7425 0.01485 0.00786 -0.0687 0.7492 1.0000
4.250 0.7668 0.01478 0.00781 -0.0669 0.7215 1.0000
4.500 0.7905 0.01474 0.00778 -0.0651 0.6916 1.0000
4.750 0.8115 0.01480 0.00786 -0.0628 0.6580 1.0000
5.000 0.8325 0.01489 0.00796 -0.0606 0.6211 1.0000
5.250 0.8515 0.01508 0.00810 -0.0581 0.5789 1.0000
5.500 0.8687 0.01537 0.00831 -0.0553 0.5298 1.0000
5.750 0.8837 0.01582 0.00857 -0.0523 0.4720 1.0000
6.000 0.8958 0.01650 0.00896 -0.0489 0.4030 1.0000
6.250 0.9047 0.01749 0.00953 -0.0453 0.3214 1.0000
6.500 0.9117 0.01885 0.01038 -0.0416 0.2353 1.0000
6.750 0.9189 0.02051 0.01149 -0.0382 0.1697 1.0000
7.000 0.9273 0.02232 0.01294 -0.0350 0.1227 1.0000
7.250 0.9386 0.02418 0.01458 -0.0322 0.0949 1.0000
7.500 0.9536 0.02614 0.01634 -0.0302 0.0781 1.0000
7.750 0.9745 0.02797 0.01821 -0.0287 0.0681 1.0000
8.000 0.9967 0.03000 0.02040 -0.0276 0.0605 1.0000
8.250 1.0195 0.03225 0.02263 -0.0269 0.0551 1.0000
8.500 1.0436 0.03558 0.02630 -0.0260 0.0528 1.0000
8.750 1.0614 0.03850 0.02970 -0.0241 0.0516 1.0000
9.000 1.0740 0.04156 0.03325 -0.0216 0.0504 1.0000
9.250 1.0825 0.04432 0.03643 -0.0189 0.0484 1.0000
9.500 1.0883 0.04734 0.03984 -0.0161 0.0471 1.0000
9.750 1.0881 0.05103 0.04396 -0.0128 0.0471 1.0000
10.000 1.0807 0.05522 0.04862 -0.0092 0.0480 1.0000
10.250 1.0692 0.05936 0.05312 -0.0056 0.0490 1.0000
10.500 1.0546 0.06322 0.05726 -0.0021 0.0500 1.0000
10.750 1.0369 0.06691 0.06115 0.0012 0.0509 1.0000
11.000 1.0184 0.07076 0.06516 0.0034 0.0515 1.0000
11.250 1.0016 0.07505 0.06957 0.0045 0.0523 1.0000
11.500 0.9886 0.08036 0.07496 0.0045 0.0533 1.0000
11.750 0.8588 0.07924 0.07433 0.0065 0.0523 1.0000
12.000 0.8353 0.08596 0.08113 0.0040 0.0529 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 795 smoothed (goe795sm-il)