GIII BL45 AIRFOIL (giiib-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL45 AIRFOIL (giiib-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.32 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiib-il-1000000.txt Download as CSV file: xf-giiib-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL45 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.9740 0.05104 0.04889 -0.0286 1.0000 0.0061
-12.500 -0.9955 0.04560 0.04324 -0.0303 1.0000 0.0061
-12.250 -1.0153 0.04130 0.03872 -0.0295 1.0000 0.0061
-12.000 -1.0327 0.03776 0.03494 -0.0271 1.0000 0.0061
-11.750 -1.0444 0.03492 0.03188 -0.0238 1.0000 0.0062
-11.500 -1.0478 0.03265 0.02942 -0.0207 1.0000 0.0063
-11.250 -1.0420 0.03078 0.02738 -0.0186 1.0000 0.0064
-11.000 -1.0318 0.02924 0.02570 -0.0168 1.0000 0.0065
-10.750 -1.0194 0.02782 0.02412 -0.0152 1.0000 0.0066
-10.500 -1.0055 0.02644 0.02259 -0.0137 1.0000 0.0068
-10.250 -0.9905 0.02508 0.02106 -0.0122 1.0000 0.0069
-10.000 -0.9747 0.02372 0.01953 -0.0108 1.0000 0.0071
-9.750 -0.9578 0.02244 0.01808 -0.0094 1.0000 0.0073
-9.500 -0.9399 0.02124 0.01673 -0.0081 1.0000 0.0076
-9.250 -0.9210 0.02015 0.01550 -0.0068 1.0000 0.0078
-9.000 -0.9012 0.01924 0.01445 -0.0056 1.0000 0.0081
-8.750 -0.8795 0.01869 0.01382 -0.0047 1.0000 0.0084
-8.500 -0.8628 0.01729 0.01224 -0.0029 1.0000 0.0088
-8.250 -0.8467 0.01605 0.01088 -0.0010 1.0000 0.0094
-8.000 -0.8273 0.01551 0.01030 0.0004 1.0000 0.0098
-7.750 -0.8084 0.01499 0.00974 0.0020 1.0000 0.0102
-7.500 -0.7910 0.01450 0.00920 0.0039 1.0000 0.0106
-7.250 -0.7587 0.01387 0.00850 0.0026 0.9975 0.0112
-7.000 -0.7242 0.01332 0.00789 0.0009 0.9947 0.0118
-6.750 -0.6925 0.01256 0.00703 -0.0002 0.9903 0.0124
-6.500 -0.6614 0.01170 0.00612 -0.0013 0.9854 0.0137
-6.250 -0.6289 0.01134 0.00575 -0.0025 0.9798 0.0149
-6.000 -0.5975 0.01097 0.00535 -0.0034 0.9722 0.0160
-5.750 -0.5673 0.01068 0.00500 -0.0040 0.9632 0.0167
-5.500 -0.5413 0.01003 0.00428 -0.0037 0.9519 0.0191
-5.000 -0.4896 0.00958 0.00376 -0.0028 0.9283 0.0230
-4.750 -0.4654 0.00918 0.00334 -0.0020 0.9173 0.0290
-4.500 -0.4402 0.00892 0.00304 -0.0015 0.9074 0.0363
-4.250 -0.4151 0.00867 0.00280 -0.0009 0.8976 0.0475
-3.750 -0.3649 0.00810 0.00239 0.0001 0.8793 0.0952
-3.500 -0.3395 0.00784 0.00221 0.0005 0.8707 0.1251
-3.250 -0.3137 0.00761 0.00206 0.0009 0.8630 0.1556
-3.000 -0.2881 0.00737 0.00192 0.0012 0.8552 0.1910
-2.750 -0.2633 0.00702 0.00176 0.0017 0.8477 0.2484
-2.500 -0.2403 0.00652 0.00159 0.0025 0.8400 0.3423
-2.250 -0.2203 0.00576 0.00137 0.0037 0.8317 0.4949
-2.000 -0.1993 0.00527 0.00126 0.0050 0.8240 0.6137
-1.750 -0.1754 0.00501 0.00119 0.0059 0.8157 0.6766
-1.500 -0.1512 0.00483 0.00113 0.0068 0.8043 0.7235
-1.250 -0.1267 0.00471 0.00108 0.0077 0.7882 0.7596
-1.000 -0.1016 0.00462 0.00105 0.0084 0.7719 0.7926
-0.750 -0.0757 0.00459 0.00103 0.0090 0.7570 0.8166
-0.500 -0.0494 0.00459 0.00102 0.0094 0.7403 0.8353
-0.250 -0.0230 0.00461 0.00101 0.0099 0.7230 0.8510
0.000 0.0036 0.00464 0.00101 0.0103 0.7039 0.8648
0.250 0.0299 0.00470 0.00102 0.0107 0.6829 0.8782
0.500 0.0562 0.00478 0.00105 0.0112 0.6626 0.8909
0.750 0.0825 0.00485 0.00109 0.0117 0.6441 0.9036
1.000 0.1086 0.00495 0.00115 0.0122 0.6266 0.9163
1.250 0.1343 0.00505 0.00121 0.0128 0.6095 0.9263
1.500 0.1622 0.00514 0.00126 0.0128 0.5921 0.9316
1.750 0.1892 0.00525 0.00131 0.0131 0.5732 0.9373
2.000 0.2159 0.00536 0.00136 0.0133 0.5524 0.9425
2.250 0.2442 0.00548 0.00143 0.0132 0.5326 0.9465
2.500 0.2714 0.00561 0.00150 0.0134 0.5120 0.9515
2.750 0.2980 0.00575 0.00157 0.0136 0.4898 0.9565
3.000 0.3274 0.00593 0.00167 0.0132 0.4613 0.9595
3.250 0.3558 0.00617 0.00177 0.0129 0.4221 0.9631
3.500 0.3814 0.00649 0.00191 0.0133 0.3698 0.9679
3.750 0.4088 0.00695 0.00209 0.0130 0.3031 0.9711
4.250 0.4721 0.00756 0.00246 0.0108 0.2402 0.9750
4.500 0.5040 0.00783 0.00265 0.0097 0.2192 0.9771
4.750 0.5352 0.00807 0.00281 0.0087 0.1999 0.9795
5.000 0.5630 0.00829 0.00297 0.0085 0.1838 0.9829
5.250 0.5974 0.00850 0.00315 0.0069 0.1711 0.9838
5.500 0.6315 0.00870 0.00332 0.0052 0.1596 0.9848
5.750 0.6652 0.00892 0.00350 0.0037 0.1475 0.9860
6.000 0.6983 0.00915 0.00369 0.0023 0.1319 0.9875
6.250 0.7292 0.00963 0.00398 0.0011 0.0922 0.9894
6.500 0.7563 0.01061 0.00462 0.0004 0.0345 0.9920
6.750 0.7850 0.01122 0.00515 -0.0001 0.0200 0.9942
7.000 0.8177 0.01163 0.00556 -0.0016 0.0165 0.9952
7.250 0.8494 0.01214 0.00614 -0.0028 0.0140 0.9965
7.500 0.8815 0.01252 0.00655 -0.0041 0.0126 0.9978
7.750 0.9126 0.01304 0.00709 -0.0052 0.0113 0.9992
8.000 0.9362 0.01391 0.00807 -0.0049 0.0102 1.0000
8.250 0.9537 0.01429 0.00850 -0.0031 0.0099 1.0000
8.500 0.9702 0.01474 0.00902 -0.0012 0.0094 1.0000
8.750 0.9859 0.01524 0.00958 0.0009 0.0090 1.0000
9.000 1.0013 0.01577 0.01015 0.0030 0.0086 1.0000
9.250 1.0164 0.01632 0.01075 0.0051 0.0083 1.0000
9.500 1.0308 0.01694 0.01142 0.0073 0.0079 1.0000
9.750 1.0403 0.01797 0.01253 0.0102 0.0074 1.0000
10.000 1.0463 0.01937 0.01407 0.0135 0.0071 1.0000
10.250 1.0636 0.01985 0.01462 0.0151 0.0069 1.0000
10.500 1.0784 0.02060 0.01545 0.0169 0.0067 1.0000
10.750 1.0922 0.02150 0.01644 0.0188 0.0065 1.0000
11.000 1.1051 0.02250 0.01753 0.0206 0.0063 1.0000
11.250 1.1170 0.02356 0.01870 0.0225 0.0061 1.0000
11.500 1.1261 0.02466 0.01989 0.0247 0.0060 1.0000
11.750 1.1333 0.02585 0.02119 0.0271 0.0058 1.0000
12.000 1.1398 0.02715 0.02260 0.0291 0.0057 1.0000
12.250 1.1458 0.02856 0.02412 0.0308 0.0056 1.0000
12.500 1.1506 0.03016 0.02583 0.0323 0.0055 1.0000
12.750 1.1546 0.03191 0.02770 0.0334 0.0054 1.0000
13.000 1.1567 0.03395 0.02986 0.0343 0.0053 1.0000
13.250 1.1577 0.03623 0.03226 0.0348 0.0053 1.0000
13.500 1.1563 0.03891 0.03506 0.0349 0.0052 1.0000
13.750 1.1525 0.04205 0.03833 0.0346 0.0051 1.0000
14.000 1.1460 0.04577 0.04219 0.0337 0.0051 1.0000
14.250 1.1368 0.05011 0.04668 0.0322 0.0050 1.0000
14.500 1.1249 0.05511 0.05183 0.0301 0.0050 1.0000
14.750 1.1117 0.06060 0.05747 0.0274 0.0050 1.0000
15.000 1.0963 0.06675 0.06379 0.0241 0.0050 1.0000
15.250 1.0801 0.07337 0.07055 0.0204 0.0050 1.0000
15.500 1.0632 0.08053 0.07785 0.0163 0.0050 1.0000
15.750 1.0463 0.08805 0.08550 0.0120 0.0050 1.0000
16.000 1.0278 0.09611 0.09369 0.0075 0.0050 1.0000
16.250 1.0075 0.10481 0.10253 0.0027 0.0051 1.0000
16.500 0.9820 0.11473 0.11260 -0.0025 0.0051 1.0000
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