GIII BL126 AIRFOIL (giiie-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL126 AIRFOIL (giiie-il) Reynolds number: 100,000 Max Cl/Cd: 44.6 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiie-il-100000-n5.txt Download as CSV file: xf-giiie-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL126 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5900 0.08902 0.08432 -0.0098 1.0000 0.0233
-8.750 -0.5951 0.08309 0.07844 -0.0149 1.0000 0.0228
-8.500 -0.6032 0.07735 0.07272 -0.0194 1.0000 0.0224
-8.250 -0.6100 0.07188 0.06719 -0.0222 1.0000 0.0219
-8.000 -0.6139 0.06620 0.06140 -0.0243 1.0000 0.0215
-7.750 -0.6151 0.06058 0.05561 -0.0254 1.0000 0.0212
-7.500 -0.6130 0.05531 0.05011 -0.0257 1.0000 0.0211
-7.250 -0.6062 0.05130 0.04588 -0.0253 1.0000 0.0219
-7.000 -0.5976 0.04736 0.04166 -0.0247 1.0000 0.0231
-6.750 -0.5881 0.04313 0.03701 -0.0235 1.0000 0.0242
-6.500 -0.5775 0.03886 0.03228 -0.0219 1.0000 0.0247
-6.250 -0.5649 0.03488 0.02778 -0.0201 1.0000 0.0250
-6.000 -0.5499 0.03141 0.02378 -0.0182 1.0000 0.0256
-5.750 -0.5325 0.02850 0.02034 -0.0163 1.0000 0.0265
-5.500 -0.5130 0.02649 0.01784 -0.0146 1.0000 0.0282
-5.250 -0.4950 0.02454 0.01574 -0.0133 1.0000 0.0310
-5.000 -0.4754 0.02307 0.01410 -0.0119 1.0000 0.0331
-4.750 -0.4557 0.02165 0.01249 -0.0104 1.0000 0.0352
-4.500 -0.4368 0.02044 0.01110 -0.0087 1.0000 0.0378
-4.250 -0.4135 0.01939 0.00994 -0.0083 0.9974 0.0431
-4.000 -0.3793 0.01838 0.00882 -0.0098 0.9899 0.0510
-3.750 -0.3460 0.01738 0.00780 -0.0113 0.9824 0.0625
-3.500 -0.3118 0.01661 0.00710 -0.0130 0.9755 0.0874
-3.250 -0.2795 0.01594 0.00653 -0.0143 0.9674 0.1230
-3.000 -0.2479 0.01529 0.00601 -0.0155 0.9594 0.1680
-2.750 -0.2172 0.01441 0.00554 -0.0168 0.9521 0.2619
-2.500 -0.2015 0.01256 0.00558 -0.0142 0.9436 0.6972
-2.250 -0.1715 0.01258 0.00571 -0.0133 0.9377 0.8027
-2.000 -0.1420 0.01269 0.00573 -0.0126 0.9299 0.8508
-1.750 -0.1063 0.01284 0.00576 -0.0132 0.9246 0.8851
-1.500 -0.0700 0.01299 0.00579 -0.0142 0.9182 0.9124
-1.250 -0.0222 0.01320 0.00584 -0.0174 0.9147 0.9405
-1.000 0.0351 0.01330 0.00580 -0.0229 0.9127 0.9619
-0.750 0.0744 0.01323 0.00563 -0.0256 0.9054 0.9679
-0.500 0.1100 0.01316 0.00546 -0.0275 0.8976 0.9731
-0.250 0.1450 0.01310 0.00534 -0.0293 0.8891 0.9783
0.000 0.1804 0.01304 0.00522 -0.0311 0.8819 0.9833
0.250 0.2150 0.01300 0.00516 -0.0329 0.8731 0.9887
0.500 0.2496 0.01296 0.00510 -0.0347 0.8653 0.9943
0.750 0.2845 0.01291 0.00505 -0.0364 0.8560 0.9994
1.000 0.3082 0.01290 0.00505 -0.0357 0.8430 1.0000
1.250 0.3298 0.01289 0.00502 -0.0344 0.8283 1.0000
1.500 0.3512 0.01289 0.00501 -0.0330 0.8137 1.0000
1.750 0.3732 0.01293 0.00506 -0.0319 0.8006 1.0000
2.000 0.3954 0.01299 0.00517 -0.0308 0.7885 1.0000
2.250 0.4177 0.01305 0.00528 -0.0298 0.7762 1.0000
2.500 0.4401 0.01312 0.00540 -0.0287 0.7637 1.0000
2.750 0.4624 0.01319 0.00554 -0.0276 0.7504 1.0000
3.000 0.4847 0.01325 0.00568 -0.0264 0.7361 1.0000
3.250 0.5070 0.01331 0.00587 -0.0252 0.7202 1.0000
3.500 0.5292 0.01335 0.00599 -0.0239 0.7020 1.0000
3.750 0.5508 0.01335 0.00608 -0.0224 0.6764 1.0000
4.000 0.5713 0.01331 0.00603 -0.0204 0.6363 1.0000
4.250 0.5911 0.01338 0.00602 -0.0182 0.5795 1.0000
4.500 0.6101 0.01368 0.00608 -0.0161 0.4989 1.0000
4.750 0.6246 0.01451 0.00627 -0.0136 0.3793 1.0000
5.000 0.6398 0.01557 0.00682 -0.0117 0.2797 1.0000
5.250 0.6547 0.01682 0.00748 -0.0100 0.1671 1.0000
5.500 0.6704 0.01816 0.00834 -0.0085 0.0939 1.0000
5.750 0.6882 0.01933 0.00933 -0.0070 0.0654 1.0000
6.000 0.7069 0.02038 0.01046 -0.0057 0.0527 1.0000
6.250 0.7247 0.02160 0.01175 -0.0041 0.0465 1.0000
6.500 0.7437 0.02270 0.01297 -0.0028 0.0411 1.0000
6.750 0.7613 0.02406 0.01433 -0.0015 0.0360 1.0000
7.000 0.7814 0.02544 0.01589 -0.0002 0.0333 1.0000
7.250 0.8021 0.02705 0.01766 0.0010 0.0308 1.0000
7.500 0.8220 0.02850 0.01918 0.0018 0.0277 1.0000
7.750 0.8415 0.03072 0.02163 0.0028 0.0252 1.0000
8.000 0.8621 0.03307 0.02434 0.0040 0.0240 1.0000
8.250 0.8801 0.03584 0.02754 0.0053 0.0230 1.0000
8.500 0.8947 0.03884 0.03100 0.0069 0.0220 1.0000
8.750 0.9065 0.04152 0.03407 0.0084 0.0205 1.0000
9.000 0.9169 0.04381 0.03665 0.0097 0.0190 1.0000
9.250 0.9238 0.04638 0.03948 0.0111 0.0180 1.0000
9.500 0.9255 0.04975 0.04318 0.0127 0.0176 1.0000
9.750 0.9223 0.05338 0.04714 0.0144 0.0174 1.0000
10.000 0.9141 0.05708 0.05113 0.0161 0.0173 1.0000
10.250 0.9005 0.06070 0.05500 0.0177 0.0172 1.0000
10.500 0.8845 0.06476 0.05929 0.0180 0.0173 1.0000
10.750 0.8661 0.06962 0.06436 0.0167 0.0174 1.0000
11.000 0.8447 0.07584 0.07080 0.0133 0.0176 1.0000
11.250 0.8181 0.08486 0.08000 0.0068 0.0181 1.0000
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Polar data table (+)
Polar graphs
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