GIII BL430 AIRFOIL (giiim-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL430 AIRFOIL (giiim-il) Reynolds number: 50,000 Max Cl/Cd: 29.65 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiim-il-50000.txt Download as CSV file: xf-giiim-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL430 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5549 0.11217 0.10511 0.0093 1.0000 0.1910
-8.500 -0.5304 0.10693 0.09986 0.0124 1.0000 0.2024
-8.250 -0.5583 0.10563 0.09873 0.0060 1.0000 0.2082
-8.000 -0.5386 0.10116 0.09427 0.0088 1.0000 0.2237
-7.750 -0.5273 0.09735 0.09051 0.0101 1.0000 0.2389
-7.500 -0.5250 0.09419 0.08742 0.0102 1.0000 0.2558
-7.250 -0.5305 0.09141 0.08475 0.0091 1.0000 0.2739
-7.000 -0.5103 0.08795 0.08130 0.0135 1.0000 0.3043
-6.750 -0.5012 0.08511 0.07853 0.0163 1.0000 0.3373
-6.500 -0.5029 0.08296 0.07648 0.0185 1.0000 0.3736
-6.250 -0.4663 0.07967 0.07317 0.0254 1.0000 0.4338
-6.000 -0.4465 0.07759 0.07112 0.0316 1.0000 0.5049
-5.750 -0.3824 0.07369 0.06714 0.0390 1.0000 0.6319
-5.500 -0.3052 0.06830 0.06165 0.0406 1.0000 0.7849
-5.250 -0.1981 0.05896 0.05216 0.0280 1.0000 0.9437
-4.250 -0.2031 0.05159 0.04512 0.0317 1.0000 0.8810
-4.000 -0.3029 0.05304 0.04690 0.0390 1.0000 0.7290
-3.750 -0.3726 0.05099 0.04520 0.0389 1.0000 0.6435
-3.500 -0.3570 0.03833 0.03103 -0.0099 1.0000 0.3381
-3.250 -0.3135 0.03538 0.02698 -0.0145 1.0000 0.2534
-3.000 -0.2833 0.03345 0.02443 -0.0145 1.0000 0.2205
-2.750 -0.2570 0.03171 0.02226 -0.0138 1.0000 0.2028
-2.500 -0.2308 0.03033 0.02043 -0.0129 1.0000 0.1877
-2.250 -0.2046 0.02955 0.01908 -0.0117 1.0000 0.1748
-2.000 -0.1811 0.02779 0.01728 -0.0109 1.0000 0.1710
-1.750 -0.1575 0.02662 0.01596 -0.0100 1.0000 0.1697
-1.500 -0.1335 0.02560 0.01480 -0.0091 1.0000 0.1681
-1.250 -0.1092 0.02474 0.01382 -0.0083 1.0000 0.1658
-1.000 -0.0847 0.02403 0.01304 -0.0075 1.0000 0.1656
-0.750 -0.0613 0.02347 0.01245 -0.0067 1.0000 0.1693
-0.500 -0.0379 0.02310 0.01200 -0.0061 1.0000 0.1727
-0.250 -0.0160 0.02285 0.01171 -0.0055 1.0000 0.1751
0.000 0.0046 0.02246 0.01143 -0.0052 1.0000 0.1808
0.250 0.0245 0.02242 0.01138 -0.0050 1.0000 0.1902
0.500 0.0449 0.02236 0.01142 -0.0053 1.0000 0.2020
0.750 0.0661 0.02241 0.01161 -0.0058 1.0000 0.2214
1.000 0.1118 0.02036 0.01215 -0.0089 0.9876 1.0000
1.250 0.1765 0.02133 0.01260 -0.0162 0.9659 1.0000
1.500 0.2435 0.02212 0.01307 -0.0241 0.9427 1.0000
1.750 0.3070 0.02260 0.01341 -0.0307 0.9143 1.0000
2.000 0.3726 0.02277 0.01356 -0.0369 0.8860 1.0000
2.250 0.4268 0.02279 0.01361 -0.0403 0.8601 1.0000
2.500 0.4620 0.02296 0.01380 -0.0405 0.8327 1.0000
2.750 0.4979 0.02290 0.01376 -0.0399 0.8061 1.0000
3.000 0.5253 0.02284 0.01372 -0.0377 0.7769 1.0000
3.250 0.5488 0.02275 0.01362 -0.0347 0.7455 1.0000
3.500 0.5714 0.02251 0.01338 -0.0312 0.7121 1.0000
3.750 0.5935 0.02218 0.01296 -0.0274 0.6764 1.0000
4.000 0.6135 0.02204 0.01273 -0.0236 0.6342 1.0000
4.250 0.6338 0.02199 0.01247 -0.0198 0.5873 1.0000
4.500 0.6535 0.02224 0.01248 -0.0164 0.5336 1.0000
4.750 0.6734 0.02273 0.01262 -0.0135 0.4782 1.0000
5.000 0.6936 0.02339 0.01293 -0.0110 0.4263 1.0000
5.250 0.7141 0.02419 0.01350 -0.0091 0.3793 1.0000
5.500 0.7356 0.02512 0.01420 -0.0075 0.3405 1.0000
5.750 0.7581 0.02630 0.01515 -0.0062 0.3095 1.0000
6.000 0.7813 0.02768 0.01630 -0.0052 0.2840 1.0000
6.250 0.8041 0.02932 0.01796 -0.0043 0.2629 1.0000
6.500 0.8268 0.03107 0.01976 -0.0034 0.2451 1.0000
6.750 0.8491 0.03295 0.02170 -0.0026 0.2302 1.0000
7.000 0.8718 0.03495 0.02368 -0.0019 0.2176 1.0000
7.250 0.8921 0.03707 0.02608 -0.0010 0.2062 1.0000
7.500 0.9097 0.03978 0.02915 -0.0002 0.1975 1.0000
7.750 0.9305 0.04210 0.03154 0.0005 0.1895 1.0000
8.000 0.9425 0.04548 0.03540 0.0014 0.1834 1.0000
8.250 0.9520 0.04921 0.03959 0.0022 0.1790 1.0000
8.500 0.9653 0.05250 0.04311 0.0028 0.1748 1.0000
8.750 0.9766 0.05628 0.04704 0.0033 0.1710 1.0000
9.000 0.9693 0.06173 0.05300 0.0035 0.1701 1.0000
9.250 0.9594 0.06760 0.05920 0.0030 0.1704 1.0000
9.500 0.9529 0.07349 0.06527 0.0023 0.1715 1.0000
9.750 0.7299 0.12140 0.11328 -0.0456 0.3620 1.0000
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Polar data table (+)
Polar graphs
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