GIII BL387 AIRFOIL (giiil-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL387 AIRFOIL (giiil-il) Reynolds number: 500,000 Max Cl/Cd: 72.22 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiil-il-500000.txt Download as CSV file: xf-giiil-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL387 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5803 0.08776 0.08544 -0.0084 1.0000 0.0227
-8.750 -0.5788 0.08385 0.08155 -0.0106 1.0000 0.0228
-8.500 -0.5798 0.07935 0.07705 -0.0148 1.0000 0.0230
-8.250 -0.5773 0.07566 0.07333 -0.0169 1.0000 0.0231
-8.000 -0.5724 0.07191 0.06956 -0.0191 1.0000 0.0234
-7.750 -0.5665 0.06808 0.06567 -0.0212 1.0000 0.0237
-7.500 -0.5592 0.06417 0.06170 -0.0230 1.0000 0.0241
-7.250 -0.5505 0.06019 0.05763 -0.0245 1.0000 0.0247
-7.000 -0.5404 0.05612 0.05345 -0.0256 1.0000 0.0254
-6.750 -0.5260 0.05040 0.04720 -0.0262 1.0000 0.0272
-6.500 -0.5201 0.04525 0.04178 -0.0252 1.0000 0.0275
-6.250 -0.5104 0.04173 0.03825 -0.0244 1.0000 0.0279
-6.000 -0.4976 0.03965 0.03614 -0.0232 1.0000 0.0282
-5.750 -0.4848 0.03779 0.03422 -0.0217 1.0000 0.0286
-5.500 -0.4728 0.03599 0.03234 -0.0198 1.0000 0.0292
-5.250 -0.4619 0.03417 0.03041 -0.0174 1.0000 0.0300
-5.000 -0.4290 0.03287 0.02857 -0.0171 0.9976 0.0332
-4.750 -0.4010 0.02744 0.02288 -0.0194 0.9943 0.0343
-4.500 -0.3695 0.02564 0.02103 -0.0212 0.9903 0.0352
-4.250 -0.3355 0.02395 0.01922 -0.0230 0.9868 0.0367
-4.000 -0.2952 0.02453 0.01943 -0.0243 0.9841 0.0407
-3.750 -0.2668 0.01789 0.01228 -0.0243 0.9790 0.0319
-3.500 -0.2326 0.01579 0.00994 -0.0254 0.9748 0.0312
-3.250 -0.1973 0.01459 0.00857 -0.0266 0.9706 0.0322
-3.000 -0.1663 0.01354 0.00739 -0.0270 0.9623 0.0326
-2.750 -0.1337 0.01286 0.00661 -0.0277 0.9554 0.0334
-2.500 -0.1067 0.01150 0.00526 -0.0274 0.9453 0.0347
-2.250 -0.0793 0.01110 0.00490 -0.0272 0.9343 0.0366
-2.000 -0.0526 0.01071 0.00448 -0.0266 0.9230 0.0384
-1.750 -0.0268 0.01032 0.00404 -0.0259 0.9108 0.0398
-1.500 -0.0010 0.01006 0.00375 -0.0252 0.8977 0.0409
-1.250 0.0229 0.00940 0.00308 -0.0242 0.8846 0.0439
-1.000 0.0486 0.00915 0.00282 -0.0236 0.8711 0.0463
-0.750 0.0744 0.00894 0.00256 -0.0228 0.8559 0.0487
-0.500 0.1001 0.00874 0.00229 -0.0221 0.8387 0.0514
-0.250 0.1257 0.00851 0.00203 -0.0214 0.8206 0.0570
0.000 0.1519 0.00840 0.00185 -0.0208 0.8024 0.0629
0.250 0.1719 0.00704 0.00158 -0.0198 0.7847 0.4389
0.500 0.1809 0.00571 0.00170 -0.0153 0.7675 0.8631
0.750 0.2042 0.00568 0.00176 -0.0134 0.7478 0.9210
1.000 0.2336 0.00578 0.00180 -0.0131 0.7257 0.9527
1.250 0.2682 0.00592 0.00183 -0.0142 0.6989 0.9725
1.500 0.3084 0.00610 0.00185 -0.0165 0.6611 0.9843
1.750 0.3587 0.00632 0.00187 -0.0212 0.6166 0.9946
2.000 0.3986 0.00650 0.00186 -0.0239 0.5772 0.9991
2.250 0.4263 0.00666 0.00187 -0.0240 0.5451 1.0000
2.500 0.4507 0.00683 0.00190 -0.0234 0.5169 1.0000
2.750 0.4751 0.00698 0.00195 -0.0229 0.4912 1.0000
3.000 0.4993 0.00716 0.00202 -0.0222 0.4647 1.0000
3.250 0.5234 0.00736 0.00211 -0.0215 0.4360 1.0000
3.500 0.5474 0.00758 0.00220 -0.0208 0.3989 1.0000
3.750 0.5705 0.00792 0.00231 -0.0200 0.3442 1.0000
4.000 0.5928 0.00839 0.00250 -0.0192 0.2852 1.0000
4.250 0.6155 0.00884 0.00273 -0.0184 0.2369 1.0000
4.500 0.6381 0.00930 0.00297 -0.0175 0.1942 1.0000
4.750 0.6612 0.00973 0.00323 -0.0168 0.1582 1.0000
5.000 0.6844 0.01015 0.00351 -0.0160 0.1304 1.0000
5.250 0.7079 0.01057 0.00381 -0.0153 0.1103 1.0000
5.500 0.7317 0.01098 0.00414 -0.0146 0.0961 1.0000
5.750 0.7560 0.01133 0.00445 -0.0140 0.0859 1.0000
6.000 0.7803 0.01172 0.00484 -0.0134 0.0780 1.0000
6.250 0.8039 0.01221 0.00527 -0.0128 0.0705 1.0000
6.500 0.8286 0.01255 0.00564 -0.0123 0.0658 1.0000
6.750 0.8527 0.01299 0.00606 -0.0117 0.0609 1.0000
7.000 0.8762 0.01352 0.00662 -0.0110 0.0572 1.0000
7.250 0.9010 0.01387 0.00700 -0.0106 0.0540 1.0000
7.500 0.9247 0.01437 0.00749 -0.0100 0.0508 1.0000
7.750 0.9471 0.01506 0.00822 -0.0093 0.0481 1.0000
8.000 0.9716 0.01544 0.00865 -0.0088 0.0460 1.0000
8.250 0.9955 0.01589 0.00914 -0.0083 0.0439 1.0000
8.500 1.0177 0.01657 0.00982 -0.0076 0.0416 1.0000
8.750 1.0393 0.01735 0.01066 -0.0069 0.0397 1.0000
9.000 1.0631 0.01780 0.01118 -0.0064 0.0380 1.0000
9.250 1.0861 0.01832 0.01176 -0.0058 0.0363 1.0000
9.500 1.1077 0.01901 0.01246 -0.0051 0.0347 1.0000
9.750 1.1259 0.02027 0.01379 -0.0040 0.0331 1.0000
10.000 1.1484 0.02081 0.01443 -0.0034 0.0319 1.0000
10.250 1.1701 0.02142 0.01512 -0.0028 0.0305 1.0000
10.500 1.1911 0.02205 0.01579 -0.0021 0.0292 1.0000
10.750 1.2087 0.02317 0.01693 -0.0011 0.0281 1.0000
11.000 1.2245 0.02463 0.01852 0.0002 0.0271 1.0000
11.250 1.2432 0.02549 0.01953 0.0011 0.0264 1.0000
11.500 1.2604 0.02649 0.02066 0.0022 0.0255 1.0000
11.750 1.2767 0.02747 0.02174 0.0033 0.0247 1.0000
12.000 1.2924 0.02837 0.02271 0.0043 0.0240 1.0000
12.250 1.3056 0.02945 0.02383 0.0056 0.0233 1.0000
12.500 1.3092 0.03167 0.02617 0.0078 0.0226 1.0000
12.750 1.3145 0.03328 0.02797 0.0098 0.0223 1.0000
13.000 1.3196 0.03482 0.02968 0.0115 0.0219 1.0000
13.250 1.3224 0.03665 0.03169 0.0130 0.0216 1.0000
13.500 1.3232 0.03878 0.03400 0.0141 0.0212 1.0000
13.750 1.3224 0.04120 0.03658 0.0149 0.0209 1.0000
14.000 1.3199 0.04396 0.03951 0.0151 0.0206 1.0000
14.250 1.3157 0.04711 0.04282 0.0148 0.0203 1.0000
14.500 1.3102 0.05063 0.04651 0.0139 0.0201 1.0000
14.750 1.3035 0.05458 0.05062 0.0124 0.0199 1.0000
15.000 1.2958 0.05891 0.05509 0.0104 0.0197 1.0000
15.250 1.2853 0.06396 0.06029 0.0077 0.0195 1.0000
15.500 1.2711 0.06985 0.06634 0.0044 0.0194 1.0000
15.750 1.2524 0.07682 0.07347 0.0003 0.0193 1.0000
16.000 1.2242 0.08587 0.08273 -0.0052 0.0194 1.0000
16.250 1.1589 0.10355 0.10078 -0.0163 0.0199 1.0000
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