GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GIII BL145 AIRFOIL (giiif-il) Reynolds number: 500,000 Max Cl/Cd: 78.93 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiif-il-500000.txt Download as CSV file: xf-giiif-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL145 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5854 0.08730 0.08517 -0.0069 1.0000 0.0147
-8.500 -0.5873 0.08237 0.08026 -0.0113 1.0000 0.0148
-8.250 -0.5928 0.07689 0.07478 -0.0172 1.0000 0.0148
-8.000 -0.5922 0.07209 0.06994 -0.0207 1.0000 0.0151
-7.750 -0.5889 0.06746 0.06524 -0.0233 1.0000 0.0154
-7.500 -0.5835 0.06292 0.06062 -0.0252 1.0000 0.0158
-7.250 -0.5759 0.05842 0.05600 -0.0265 1.0000 0.0165
-7.000 -0.5662 0.05384 0.05128 -0.0272 1.0000 0.0175
-6.750 -0.5423 0.05049 0.04770 -0.0271 1.0000 0.0198
-6.500 -0.5307 0.04629 0.04328 -0.0262 1.0000 0.0199
-5.250 -0.4723 0.02068 0.01578 -0.0185 0.9933 0.0166
-5.000 -0.4417 0.01616 0.01056 -0.0186 0.9890 0.0156
-4.750 -0.4069 0.01452 0.00869 -0.0201 0.9854 0.0167
-4.500 -0.3710 0.01326 0.00726 -0.0218 0.9826 0.0180
-4.250 -0.3383 0.01257 0.00648 -0.0228 0.9757 0.0196
-4.000 -0.3067 0.01111 0.00488 -0.0238 0.9700 0.0225
-3.750 -0.2765 0.01050 0.00422 -0.0243 0.9609 0.0256
-3.500 -0.2458 0.01007 0.00372 -0.0249 0.9523 0.0293
-3.250 -0.2185 0.00954 0.00317 -0.0248 0.9418 0.0403
-3.000 -0.1929 0.00912 0.00280 -0.0243 0.9303 0.0598
-2.750 -0.1669 0.00890 0.00258 -0.0239 0.9195 0.0764
-2.500 -0.1410 0.00871 0.00237 -0.0235 0.9094 0.0938
-2.250 -0.1157 0.00845 0.00217 -0.0230 0.8997 0.1211
-2.000 -0.0920 0.00790 0.00198 -0.0224 0.8892 0.2179
-1.750 -0.0805 0.00604 0.00173 -0.0199 0.8788 0.6792
-1.500 -0.0572 0.00587 0.00172 -0.0186 0.8707 0.7583
-1.250 -0.0327 0.00579 0.00172 -0.0177 0.8617 0.8001
-1.000 -0.0075 0.00575 0.00170 -0.0169 0.8535 0.8268
-0.750 0.0175 0.00574 0.00169 -0.0159 0.8447 0.8504
-0.500 0.0426 0.00573 0.00169 -0.0151 0.8340 0.8709
-0.250 0.0678 0.00573 0.00168 -0.0142 0.8237 0.8879
0.000 0.0927 0.00576 0.00169 -0.0132 0.8146 0.9055
0.250 0.1179 0.00579 0.00172 -0.0124 0.8049 0.9220
0.500 0.1427 0.00584 0.00177 -0.0113 0.7954 0.9404
0.750 0.1707 0.00591 0.00181 -0.0111 0.7867 0.9534
1.000 0.2025 0.00595 0.00183 -0.0119 0.7777 0.9600
1.250 0.2333 0.00599 0.00185 -0.0125 0.7689 0.9677
1.500 0.2678 0.00605 0.00186 -0.0140 0.7605 0.9721
1.750 0.3030 0.00607 0.00191 -0.0157 0.7505 0.9770
2.000 0.3368 0.00611 0.00195 -0.0171 0.7408 0.9826
2.250 0.3744 0.00615 0.00198 -0.0194 0.7304 0.9855
2.500 0.4101 0.00617 0.00197 -0.0211 0.7065 0.9898
2.750 0.4446 0.00623 0.00195 -0.0226 0.6701 0.9946
3.000 0.4812 0.00631 0.00198 -0.0247 0.6417 0.9982
3.250 0.5107 0.00647 0.00202 -0.0253 0.6003 1.0000
3.500 0.5328 0.00678 0.00209 -0.0244 0.5260 1.0000
3.750 0.5516 0.00757 0.00231 -0.0231 0.3932 1.0000
4.000 0.5712 0.00829 0.00262 -0.0220 0.2947 1.0000
4.250 0.5881 0.00935 0.00303 -0.0207 0.1531 1.0000
4.500 0.6057 0.01034 0.00355 -0.0192 0.0606 1.0000
4.750 0.6261 0.01103 0.00414 -0.0179 0.0376 1.0000
5.000 0.6483 0.01146 0.00462 -0.0169 0.0310 1.0000
5.250 0.6687 0.01220 0.00541 -0.0156 0.0259 1.0000
5.500 0.6909 0.01272 0.00601 -0.0146 0.0235 1.0000
5.750 0.7127 0.01336 0.00669 -0.0135 0.0213 1.0000
6.000 0.7324 0.01436 0.00775 -0.0122 0.0188 1.0000
6.250 0.7518 0.01565 0.00917 -0.0108 0.0171 1.0000
6.500 0.7743 0.01652 0.01013 -0.0099 0.0162 1.0000
6.750 0.7964 0.01764 0.01136 -0.0089 0.0151 1.0000
7.000 0.8186 0.01896 0.01281 -0.0079 0.0142 1.0000
7.250 0.8407 0.02039 0.01438 -0.0070 0.0134 1.0000
7.500 0.8624 0.02140 0.01546 -0.0064 0.0123 1.0000
7.750 0.8777 0.02542 0.01984 -0.0048 0.0114 1.0000
8.000 0.8907 0.02963 0.02450 -0.0029 0.0113 1.0000
8.250 0.9010 0.03353 0.02886 -0.0009 0.0112 1.0000
8.500 0.9103 0.03696 0.03266 0.0011 0.0111 1.0000
8.750 0.9274 0.03884 0.03469 0.0022 0.0116 1.0000
17.250 0.8469 0.22165 0.21931 -0.0712 0.0091 1.0000
17.500 0.8543 0.22541 0.22306 -0.0733 0.0086 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GIII BL145 AIRFOIL (giiif-il)