GIII BL450 AIRFOIL (giiin-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL450 AIRFOIL (giiin-il) Reynolds number: 100,000 Max Cl/Cd: 41.88 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiin-il-100000.txt Download as CSV file: xf-giiin-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL450 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5118 0.08843 0.08351 0.0007 1.0000 0.0725
-7.250 -0.5081 0.08425 0.07928 -0.0064 1.0000 0.0747
-7.000 -0.5099 0.08241 0.07697 -0.0158 1.0000 0.0760
-6.750 -0.4938 0.07571 0.07059 -0.0135 1.0000 0.0771
-6.500 -0.4811 0.07194 0.06690 -0.0127 1.0000 0.0788
-6.250 -0.4685 0.06852 0.06346 -0.0136 1.0000 0.0813
-6.000 -0.4542 0.06527 0.06007 -0.0161 1.0000 0.0854
-5.750 -0.4401 0.06211 0.05654 -0.0190 1.0000 0.0887
-5.500 -0.4257 0.05800 0.05260 -0.0184 1.0000 0.0910
-5.250 -0.4090 0.05521 0.04975 -0.0187 1.0000 0.0965
-5.000 -0.3920 0.05226 0.04652 -0.0198 1.0000 0.1026
-4.750 -0.3758 0.04917 0.04351 -0.0194 1.0000 0.1070
-4.500 -0.3577 0.04711 0.04109 -0.0197 1.0000 0.1160
-4.250 -0.3423 0.04399 0.03809 -0.0189 1.0000 0.1209
-4.000 -0.3273 0.04188 0.03577 -0.0182 1.0000 0.1318
-3.750 -0.3136 0.04036 0.03406 -0.0169 1.0000 0.1458
-3.500 -0.3012 0.03766 0.03152 -0.0154 1.0000 0.1543
-3.250 -0.2913 0.03586 0.02960 -0.0139 1.0000 0.1800
-3.000 -0.2809 0.03366 0.02754 -0.0123 1.0000 0.2027
-2.750 -0.2808 0.01989 0.01418 -0.0089 0.9974 0.2283
-2.500 -0.2467 0.01563 0.01021 -0.0121 0.9887 0.2717
-2.250 -0.2029 0.01307 0.00755 -0.0161 0.9772 0.3138
-2.000 -0.1556 0.01075 0.00503 -0.0202 0.9660 0.3319
-1.750 -0.0982 0.00876 0.00263 -0.0255 0.9573 0.3116
-1.500 -0.0324 0.00868 0.00139 -0.0288 0.9462 0.1882
-1.250 0.0205 0.00854 0.00058 -0.0307 0.9328 0.1446
-1.000 0.0304 0.02173 0.01331 -0.0274 0.9512 0.1362
-0.750 0.0821 0.02076 0.01212 -0.0306 0.9381 0.1232
-0.500 0.1274 0.01976 0.01107 -0.0330 0.9230 0.1222
-0.250 0.1650 0.01900 0.01029 -0.0338 0.9046 0.1204
0.000 0.1958 0.01839 0.00968 -0.0331 0.8831 0.1205
0.250 0.2216 0.01784 0.00917 -0.0313 0.8611 0.1243
0.500 0.2436 0.01740 0.00874 -0.0288 0.8372 0.1264
0.750 0.2653 0.01702 0.00832 -0.0263 0.8140 0.1286
1.000 0.2865 0.01645 0.00777 -0.0240 0.7931 0.1351
1.250 0.3101 0.01617 0.00740 -0.0222 0.7735 0.1417
1.500 0.3345 0.01589 0.00705 -0.0207 0.7535 0.1514
1.750 0.3595 0.01560 0.00679 -0.0194 0.7330 0.1760
2.000 0.4103 0.01325 0.00668 -0.0218 0.7096 1.0000
2.250 0.4337 0.01334 0.00650 -0.0200 0.6887 1.0000
2.500 0.4570 0.01345 0.00639 -0.0184 0.6668 1.0000
2.750 0.4805 0.01360 0.00637 -0.0170 0.6427 1.0000
3.000 0.5039 0.01375 0.00633 -0.0155 0.6186 1.0000
3.250 0.5274 0.01393 0.00638 -0.0141 0.5912 1.0000
3.500 0.5508 0.01411 0.00639 -0.0127 0.5622 1.0000
3.750 0.5740 0.01432 0.00643 -0.0113 0.5279 1.0000
4.000 0.5969 0.01455 0.00651 -0.0100 0.4858 1.0000
4.250 0.6194 0.01486 0.00660 -0.0086 0.4356 1.0000
4.500 0.6416 0.01532 0.00677 -0.0074 0.3801 1.0000
4.750 0.6640 0.01593 0.00704 -0.0064 0.3308 1.0000
5.000 0.6862 0.01672 0.00745 -0.0054 0.2937 1.0000
5.250 0.7089 0.01761 0.00809 -0.0046 0.2641 1.0000
5.500 0.7320 0.01859 0.00888 -0.0039 0.2403 1.0000
5.750 0.7555 0.01956 0.00972 -0.0032 0.2203 1.0000
6.000 0.7792 0.02054 0.01059 -0.0025 0.2035 1.0000
6.250 0.8033 0.02156 0.01153 -0.0020 0.1896 1.0000
6.500 0.8274 0.02263 0.01248 -0.0014 0.1778 1.0000
6.750 0.8516 0.02354 0.01341 -0.0009 0.1670 1.0000
7.000 0.8757 0.02470 0.01464 -0.0003 0.1580 1.0000
7.250 0.8999 0.02579 0.01562 0.0001 0.1501 1.0000
7.500 0.9234 0.02711 0.01715 0.0008 0.1430 1.0000
7.750 0.9471 0.02821 0.01823 0.0012 0.1366 1.0000
8.000 0.9697 0.02987 0.02006 0.0018 0.1312 1.0000
8.250 0.9919 0.03132 0.02175 0.0025 0.1259 1.0000
8.500 1.0150 0.03275 0.02310 0.0028 0.1213 1.0000
8.750 1.0336 0.03493 0.02567 0.0036 0.1174 1.0000
9.000 1.0515 0.03709 0.02822 0.0045 0.1138 1.0000
9.250 1.0720 0.03873 0.02994 0.0051 0.1101 1.0000
9.500 1.0919 0.04130 0.03243 0.0053 0.1069 1.0000
9.750 1.0999 0.04438 0.03615 0.0066 0.1051 1.0000
10.000 1.1040 0.04818 0.04050 0.0077 0.1034 1.0000
10.250 1.1035 0.05231 0.04511 0.0086 0.1018 1.0000
10.500 1.0974 0.05678 0.04998 0.0094 0.1006 1.0000
10.750 1.0798 0.06218 0.05575 0.0097 0.1003 1.0000
11.000 1.0406 0.06916 0.06303 0.0090 0.1016 1.0000
11.250 0.9908 0.07879 0.07286 0.0037 0.1040 1.0000
11.500 0.9581 0.08873 0.08288 -0.0025 0.1057 1.0000
11.750 0.9405 0.09757 0.09177 -0.0071 0.1073 1.0000
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Polar data table (+)
Polar graphs
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