GIII BL430 AIRFOIL (giiim-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL430 AIRFOIL (giiim-il) Reynolds number: 100,000 Max Cl/Cd: 43.16 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiim-il-100000.txt Download as CSV file: xf-giiim-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5237 0.09217 0.08714 -0.0003 1.0000 0.0758
-7.750 -0.5240 0.08812 0.08314 -0.0045 1.0000 0.0778
-7.500 -0.5260 0.08383 0.07877 -0.0126 1.0000 0.0805
-7.250 -0.5340 0.08224 0.07672 -0.0201 1.0000 0.0818
-7.000 -0.5146 0.07498 0.06988 -0.0166 1.0000 0.0840
-6.750 -0.5027 0.07171 0.06665 -0.0159 1.0000 0.0871
-6.500 -0.4925 0.06828 0.06314 -0.0178 1.0000 0.0915
-6.250 -0.4857 0.06530 0.05969 -0.0220 1.0000 0.0965
-6.000 -0.4713 0.06071 0.05531 -0.0209 1.0000 0.0989
-5.750 -0.4570 0.05768 0.05229 -0.0207 1.0000 0.1033
-5.500 -0.4439 0.05518 0.04935 -0.0222 1.0000 0.1120
-5.250 -0.4291 0.05142 0.04577 -0.0213 1.0000 0.1158
-5.000 -0.4145 0.04950 0.04347 -0.0214 1.0000 0.1277
-4.750 -0.3997 0.04604 0.04021 -0.0204 1.0000 0.1332
-4.500 -0.3862 0.04357 0.03762 -0.0196 1.0000 0.1471
-4.250 -0.3734 0.04126 0.03529 -0.0184 1.0000 0.1640
-4.000 -0.3609 0.03916 0.03319 -0.0170 1.0000 0.1846
-3.750 -0.3510 0.03699 0.03106 -0.0153 1.0000 0.2141
-3.500 -0.3411 0.03500 0.02912 -0.0133 1.0000 0.2465
-3.250 -0.3306 0.03304 0.02724 -0.0112 1.0000 0.2797
-3.000 -0.3187 0.03113 0.02539 -0.0091 1.0000 0.3123
-2.750 -0.3028 0.02979 0.02395 -0.0075 1.0000 0.3407
-2.500 -0.2880 0.02742 0.02176 -0.0056 1.0000 0.3683
-2.250 -0.2627 0.02560 0.01971 -0.0059 1.0000 0.3688
-2.000 -0.2055 0.02483 0.01729 -0.0087 1.0000 0.2119
-1.750 -0.1705 0.02433 0.01602 -0.0068 1.0000 0.1386
-1.500 -0.1457 0.02370 0.01504 -0.0057 1.0000 0.1246
-1.250 -0.0947 0.02233 0.01331 -0.0093 0.9915 0.1117
-1.000 -0.0430 0.02106 0.01197 -0.0136 0.9815 0.1088
-0.750 0.0098 0.02011 0.01094 -0.0181 0.9706 0.1099
-0.500 0.0611 0.01906 0.00994 -0.0223 0.9584 0.1100
-0.250 0.1093 0.01785 0.00897 -0.0261 0.9455 0.1148
0.000 0.1548 0.01709 0.00836 -0.0291 0.9306 0.1206
0.250 0.1968 0.01652 0.00780 -0.0311 0.9136 0.1276
0.500 0.2346 0.01595 0.00724 -0.0320 0.8939 0.1426
0.750 0.2638 0.01532 0.00678 -0.0310 0.8695 0.1803
1.000 0.3346 0.01280 0.00650 -0.0358 0.8489 1.0000
1.250 0.3567 0.01285 0.00634 -0.0336 0.8255 1.0000
1.500 0.3778 0.01296 0.00631 -0.0317 0.8003 1.0000
1.750 0.3995 0.01304 0.00624 -0.0297 0.7777 1.0000
2.000 0.4213 0.01313 0.00620 -0.0279 0.7547 1.0000
2.250 0.4433 0.01321 0.00617 -0.0261 0.7302 1.0000
2.500 0.4656 0.01327 0.00609 -0.0242 0.7066 1.0000
2.750 0.4880 0.01336 0.00608 -0.0225 0.6803 1.0000
3.000 0.5108 0.01347 0.00605 -0.0209 0.6544 1.0000
3.250 0.5336 0.01362 0.00606 -0.0193 0.6270 1.0000
3.500 0.5564 0.01380 0.00614 -0.0178 0.5968 1.0000
3.750 0.5791 0.01401 0.00622 -0.0163 0.5640 1.0000
4.000 0.6015 0.01427 0.00632 -0.0148 0.5276 1.0000
4.250 0.6235 0.01457 0.00648 -0.0133 0.4829 1.0000
4.500 0.6448 0.01494 0.00663 -0.0117 0.4287 1.0000
4.750 0.6656 0.01545 0.00683 -0.0103 0.3638 1.0000
5.000 0.6860 0.01626 0.00721 -0.0090 0.3078 1.0000
5.250 0.7065 0.01729 0.00787 -0.0078 0.2677 1.0000
5.500 0.7283 0.01830 0.00864 -0.0069 0.2374 1.0000
5.750 0.7508 0.01933 0.00949 -0.0060 0.2139 1.0000
6.000 0.7739 0.02032 0.01038 -0.0053 0.1952 1.0000
6.250 0.7972 0.02131 0.01131 -0.0046 0.1797 1.0000
6.500 0.8208 0.02235 0.01230 -0.0039 0.1669 1.0000
6.750 0.8445 0.02349 0.01328 -0.0033 0.1559 1.0000
7.000 0.8682 0.02444 0.01436 -0.0027 0.1457 1.0000
7.250 0.8918 0.02574 0.01572 -0.0020 0.1372 1.0000
7.500 0.9155 0.02695 0.01687 -0.0015 0.1298 1.0000
7.750 0.9382 0.02849 0.01862 -0.0008 0.1231 1.0000
8.000 0.9610 0.02981 0.02004 -0.0002 0.1172 1.0000
8.250 0.9832 0.03187 0.02216 0.0004 0.1127 1.0000
8.500 1.0028 0.03360 0.02430 0.0014 0.1079 1.0000
8.750 1.0239 0.03521 0.02600 0.0020 0.1038 1.0000
9.000 1.0443 0.03795 0.02876 0.0024 0.1008 1.0000
9.250 1.0565 0.04057 0.03199 0.0039 0.0985 1.0000
9.500 1.0668 0.04354 0.03547 0.0052 0.0960 1.0000
9.750 1.0758 0.04666 0.03898 0.0064 0.0938 1.0000
10.000 1.0803 0.05042 0.04313 0.0075 0.0928 1.0000
10.250 1.0773 0.05491 0.04804 0.0087 0.0925 1.0000
10.500 1.0613 0.06051 0.05409 0.0096 0.0929 1.0000
10.750 1.0270 0.06729 0.06125 0.0099 0.0945 1.0000
11.000 0.9824 0.07510 0.06929 0.0074 0.0967 1.0000
11.250 0.9479 0.08404 0.07833 0.0020 0.0986 1.0000
11.500 0.9355 0.09111 0.08543 -0.0011 0.0999 1.0000
11.750 0.9381 0.09638 0.09070 -0.0017 0.1006 1.0000
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Polar data table (+)
Polar graphs
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