GIII BL332 AIRFOIL (giiij-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GIII BL332 AIRFOIL (giiij-il) Reynolds number: 200,000 Max Cl/Cd: 59.78 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiij-il-200000.txt Download as CSV file: xf-giiij-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL332 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5635 0.09049 0.08693 -0.0082 1.0000 0.0426
-8.500 -0.5680 0.08489 0.08137 -0.0155 1.0000 0.0435
-8.000 -0.5787 0.07585 0.07196 -0.0266 1.0000 0.0449
-7.750 -0.5762 0.07265 0.06853 -0.0274 1.0000 0.0451
-7.500 -0.5736 0.06459 0.06064 -0.0279 1.0000 0.0465
-7.250 -0.5631 0.06139 0.05747 -0.0275 1.0000 0.0475
-7.000 -0.5529 0.05830 0.05433 -0.0274 1.0000 0.0487
-6.750 -0.5424 0.05516 0.05109 -0.0273 1.0000 0.0504
-6.500 -0.5311 0.05198 0.04775 -0.0270 1.0000 0.0527
-6.250 -0.5161 0.05210 0.04716 -0.0252 1.0000 0.0574
-6.000 -0.5122 0.04534 0.04036 -0.0245 1.0000 0.0589
-5.750 -0.4996 0.04231 0.03741 -0.0235 1.0000 0.0605
-5.500 -0.4868 0.04012 0.03519 -0.0220 1.0000 0.0628
-5.250 -0.4736 0.03823 0.03311 -0.0201 1.0000 0.0671
-5.000 -0.4638 0.03592 0.03036 -0.0175 1.0000 0.0734
-4.750 -0.4504 0.03380 0.02833 -0.0161 1.0000 0.0766
-4.500 -0.4380 0.03263 0.02676 -0.0137 1.0000 0.0876
-4.250 -0.4232 0.03041 0.02466 -0.0125 1.0000 0.0915
-4.000 -0.4084 0.02899 0.02298 -0.0108 1.0000 0.1034
-3.500 -0.3743 0.02618 0.02004 -0.0083 1.0000 0.1253
-3.250 -0.3344 0.02181 0.01439 -0.0050 1.0000 0.0563
-3.000 -0.2932 0.02004 0.01235 -0.0074 0.9961 0.0565
-2.750 -0.2535 0.01811 0.01023 -0.0095 0.9926 0.0556
-2.500 -0.2149 0.01687 0.00885 -0.0114 0.9883 0.0561
-2.250 -0.1756 0.01564 0.00757 -0.0137 0.9847 0.0593
-2.000 -0.1393 0.01463 0.00663 -0.0156 0.9795 0.0625
-1.750 -0.1007 0.01395 0.00598 -0.0179 0.9741 0.0670
-1.500 -0.0600 0.01336 0.00541 -0.0206 0.9697 0.0723
-1.250 -0.0249 0.01274 0.00483 -0.0223 0.9620 0.0795
-1.000 0.0177 0.01225 0.00439 -0.0254 0.9575 0.0984
-0.750 0.0287 0.00948 0.00448 -0.0216 0.9491 0.8294
-0.500 0.0706 0.00966 0.00483 -0.0215 0.9466 0.9557
-0.250 0.1529 0.00974 0.00479 -0.0316 0.9511 0.9854
0.000 0.2237 0.00955 0.00453 -0.0403 0.9498 1.0000
0.250 0.2563 0.00941 0.00435 -0.0413 0.9352 1.0000
0.500 0.2826 0.00928 0.00419 -0.0409 0.9183 1.0000
0.750 0.3052 0.00918 0.00405 -0.0396 0.9009 1.0000
1.000 0.3270 0.00910 0.00392 -0.0382 0.8840 1.0000
1.250 0.3485 0.00904 0.00381 -0.0366 0.8671 1.0000
1.500 0.3698 0.00900 0.00373 -0.0351 0.8489 1.0000
1.750 0.3912 0.00897 0.00367 -0.0335 0.8286 1.0000
2.000 0.4132 0.00894 0.00359 -0.0320 0.8085 1.0000
2.250 0.4353 0.00893 0.00352 -0.0305 0.7854 1.0000
2.500 0.4571 0.00893 0.00343 -0.0289 0.7567 1.0000
2.750 0.4794 0.00898 0.00339 -0.0274 0.7257 1.0000
3.000 0.5023 0.00906 0.00339 -0.0261 0.6951 1.0000
3.250 0.5252 0.00919 0.00342 -0.0249 0.6621 1.0000
3.500 0.5480 0.00936 0.00348 -0.0237 0.6247 1.0000
3.750 0.5702 0.00958 0.00356 -0.0224 0.5806 1.0000
4.000 0.5918 0.00990 0.00367 -0.0211 0.5300 1.0000
4.250 0.6128 0.01032 0.00385 -0.0197 0.4773 1.0000
4.500 0.6335 0.01079 0.00411 -0.0184 0.4143 1.0000
4.750 0.6526 0.01146 0.00440 -0.0169 0.3304 1.0000
5.000 0.6701 0.01246 0.00486 -0.0155 0.2283 1.0000
5.250 0.6879 0.01359 0.00551 -0.0141 0.1527 1.0000
5.500 0.7083 0.01447 0.00619 -0.0130 0.1205 1.0000
5.750 0.7293 0.01529 0.00692 -0.0120 0.1027 1.0000
6.000 0.7507 0.01608 0.00767 -0.0110 0.0899 1.0000
6.250 0.7717 0.01702 0.00859 -0.0100 0.0807 1.0000
6.500 0.7920 0.01818 0.00964 -0.0089 0.0727 1.0000
6.750 0.8153 0.01886 0.01046 -0.0081 0.0667 1.0000
7.000 0.8372 0.01991 0.01147 -0.0073 0.0619 1.0000
7.250 0.8595 0.02134 0.01297 -0.0065 0.0582 1.0000
7.500 0.8828 0.02223 0.01398 -0.0057 0.0543 1.0000
7.750 0.9054 0.02333 0.01511 -0.0051 0.0512 1.0000
8.000 0.9274 0.02597 0.01782 -0.0045 0.0487 1.0000
8.250 0.9497 0.02720 0.01933 -0.0035 0.0472 1.0000
8.500 0.9710 0.02864 0.02104 -0.0026 0.0450 1.0000
8.750 0.9914 0.03021 0.02282 -0.0017 0.0430 1.0000
9.000 1.0106 0.03214 0.02496 -0.0007 0.0418 1.0000
9.250 1.0279 0.03439 0.02743 0.0003 0.0407 1.0000
9.500 1.0419 0.03759 0.03086 0.0013 0.0397 1.0000
9.750 1.0459 0.04253 0.03624 0.0031 0.0389 1.0000
10.000 1.0519 0.04480 0.03898 0.0052 0.0382 1.0000
10.250 1.0514 0.04873 0.04333 0.0072 0.0380 1.0000
10.500 1.0452 0.05313 0.04810 0.0091 0.0381 1.0000
10.750 1.0345 0.05777 0.05303 0.0109 0.0384 1.0000
11.000 0.9485 0.05268 0.04819 0.0197 0.0391 1.0000
11.250 0.9302 0.05559 0.05128 0.0215 0.0393 1.0000
11.500 0.8018 0.07154 0.06795 0.0147 0.0445 1.0000
11.750 0.7599 0.08270 0.07918 0.0089 0.0467 1.0000
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Polar data table (+)
Polar graphs
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