GIII BL430 AIRFOIL (giiim-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GIII BL430 AIRFOIL (giiim-il) Reynolds number: 100,000 Max Cl/Cd: 41.44 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiim-il-100000-n5.txt Download as CSV file: xf-giiim-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5397 0.10142 0.09621 -0.0007 1.0000 0.0507
-8.500 -0.5426 0.09681 0.09164 -0.0067 1.0000 0.0508
-8.250 -0.5452 0.09232 0.08711 -0.0121 1.0000 0.0509
-8.000 -0.5445 0.08809 0.08278 -0.0159 1.0000 0.0510
-7.750 -0.5312 0.08386 0.07870 -0.0136 1.0000 0.0516
-7.500 -0.5222 0.08033 0.07519 -0.0134 1.0000 0.0522
-7.250 -0.5144 0.07669 0.07155 -0.0146 1.0000 0.0530
-7.000 -0.5061 0.07298 0.06780 -0.0162 1.0000 0.0539
-6.750 -0.4968 0.06935 0.06410 -0.0179 1.0000 0.0554
-6.500 -0.4869 0.06600 0.06033 -0.0219 1.0000 0.0593
-6.250 -0.4761 0.06190 0.05607 -0.0226 1.0000 0.0601
-6.000 -0.4627 0.05823 0.05255 -0.0222 1.0000 0.0615
-5.750 -0.4483 0.05525 0.04953 -0.0221 1.0000 0.0631
-5.500 -0.4329 0.05229 0.04644 -0.0221 1.0000 0.0647
-5.250 -0.4164 0.04948 0.04343 -0.0220 1.0000 0.0667
-5.000 -0.3970 0.04464 0.03807 -0.0211 1.0000 0.0498
-4.750 -0.3810 0.04163 0.03493 -0.0202 1.0000 0.0472
-4.500 -0.3638 0.03917 0.03226 -0.0191 1.0000 0.0476
-4.250 -0.3465 0.03690 0.02975 -0.0177 1.0000 0.0480
-4.000 -0.3291 0.03457 0.02718 -0.0162 1.0000 0.0470
-3.750 -0.3111 0.03231 0.02461 -0.0145 1.0000 0.0460
-3.500 -0.2930 0.03039 0.02242 -0.0129 1.0000 0.0457
-3.250 -0.2599 0.02864 0.02043 -0.0143 0.9933 0.0477
-3.000 -0.2220 0.02674 0.01817 -0.0162 0.9849 0.0489
-2.750 -0.1848 0.02495 0.01606 -0.0179 0.9757 0.0491
-2.500 -0.1472 0.02364 0.01433 -0.0193 0.9659 0.0508
-2.250 -0.1120 0.02222 0.01292 -0.0210 0.9556 0.0528
-2.000 -0.0754 0.02104 0.01161 -0.0225 0.9454 0.0537
-1.750 -0.0406 0.02000 0.01050 -0.0236 0.9329 0.0548
-1.500 -0.0069 0.01922 0.00963 -0.0243 0.9191 0.0576
-1.250 0.0261 0.01855 0.00885 -0.0248 0.9049 0.0596
-1.000 0.0569 0.01763 0.00801 -0.0251 0.8905 0.0609
-0.750 0.0859 0.01695 0.00741 -0.0249 0.8748 0.0629
-0.500 0.1132 0.01646 0.00696 -0.0244 0.8579 0.0666
-0.250 0.1396 0.01607 0.00654 -0.0236 0.8402 0.0695
0.000 0.1648 0.01562 0.00609 -0.0226 0.8223 0.0719
0.250 0.1905 0.01531 0.00576 -0.0218 0.8036 0.0762
0.500 0.2163 0.01511 0.00546 -0.0208 0.7822 0.0822
0.750 0.2413 0.01485 0.00514 -0.0196 0.7557 0.0887
1.000 0.2663 0.01465 0.00486 -0.0184 0.7262 0.1009
1.250 0.2880 0.01331 0.00458 -0.0174 0.6987 0.4664
1.750 0.3756 0.01223 0.00461 -0.0210 0.6461 1.0000
2.000 0.3995 0.01238 0.00459 -0.0200 0.6218 1.0000
2.250 0.4232 0.01256 0.00460 -0.0189 0.5974 1.0000
2.500 0.4469 0.01276 0.00463 -0.0179 0.5714 1.0000
2.750 0.4705 0.01299 0.00468 -0.0168 0.5456 1.0000
3.000 0.4943 0.01322 0.00479 -0.0159 0.5187 1.0000
3.250 0.5181 0.01348 0.00491 -0.0149 0.4914 1.0000
3.500 0.5419 0.01375 0.00505 -0.0140 0.4616 1.0000
3.750 0.5656 0.01403 0.00522 -0.0131 0.4277 1.0000
4.000 0.5893 0.01434 0.00540 -0.0123 0.3861 1.0000
4.250 0.6121 0.01477 0.00558 -0.0114 0.3330 1.0000
4.500 0.6343 0.01535 0.00586 -0.0105 0.2863 1.0000
4.750 0.6568 0.01598 0.00626 -0.0097 0.2502 1.0000
5.000 0.6796 0.01659 0.00671 -0.0090 0.2221 1.0000
5.250 0.7026 0.01720 0.00721 -0.0083 0.1996 1.0000
5.500 0.7257 0.01780 0.00774 -0.0077 0.1797 1.0000
5.750 0.7488 0.01840 0.00828 -0.0070 0.1631 1.0000
6.000 0.7719 0.01902 0.00884 -0.0063 0.1487 1.0000
6.250 0.7946 0.01968 0.00944 -0.0057 0.1369 1.0000
6.500 0.8169 0.02039 0.01008 -0.0050 0.1267 1.0000
6.750 0.8399 0.02104 0.01078 -0.0043 0.1172 1.0000
7.000 0.8620 0.02181 0.01152 -0.0036 0.1096 1.0000
7.250 0.8843 0.02255 0.01230 -0.0029 0.1024 1.0000
7.500 0.9060 0.02342 0.01316 -0.0022 0.0966 1.0000
7.750 0.9281 0.02422 0.01402 -0.0015 0.0907 1.0000
8.000 0.9489 0.02520 0.01495 -0.0008 0.0864 1.0000
8.250 0.9710 0.02613 0.01605 -0.0001 0.0818 1.0000
8.500 0.9920 0.02706 0.01702 0.0006 0.0777 1.0000
8.750 1.0122 0.02817 0.01812 0.0013 0.0744 1.0000
9.000 1.0331 0.02933 0.01949 0.0021 0.0711 1.0000
9.250 1.0532 0.03046 0.02073 0.0029 0.0681 1.0000
9.500 1.0725 0.03158 0.02185 0.0036 0.0656 1.0000
9.750 1.0911 0.03300 0.02343 0.0044 0.0632 1.0000
10.000 1.1089 0.03452 0.02521 0.0052 0.0609 1.0000
10.250 1.1260 0.03604 0.02690 0.0061 0.0590 1.0000
10.500 1.1425 0.03743 0.02838 0.0069 0.0573 1.0000
10.750 1.1587 0.03888 0.02983 0.0077 0.0558 1.0000
11.000 1.1697 0.04098 0.03227 0.0088 0.0542 1.0000
11.250 1.1780 0.04325 0.03489 0.0101 0.0527 1.0000
11.500 1.1840 0.04563 0.03755 0.0113 0.0515 1.0000
11.750 1.1872 0.04807 0.04024 0.0126 0.0506 1.0000
12.000 1.1862 0.05047 0.04286 0.0141 0.0498 1.0000
12.250 1.1835 0.05300 0.04557 0.0152 0.0492 1.0000
12.500 1.1797 0.05570 0.04843 0.0158 0.0486 1.0000
12.750 1.1760 0.05859 0.05144 0.0159 0.0480 1.0000
13.000 1.1719 0.06176 0.05470 0.0156 0.0475 1.0000
13.250 1.1514 0.06707 0.06028 0.0135 0.0472 1.0000
13.500 1.1241 0.07406 0.06755 0.0095 0.0472 1.0000
13.750 1.0917 0.08285 0.07659 0.0036 0.0473 1.0000
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Polar data table (+)
Polar graphs
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