GIII BL387 AIRFOIL (giiil-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL387 AIRFOIL (giiil-il) Reynolds number: 100,000 Max Cl/Cd: 42.25 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiil-il-100000-n5.txt Download as CSV file: xf-giiil-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL387 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5610 0.10787 0.10262 -0.0034 1.0000 0.0538
-9.250 -0.5659 0.10330 0.09809 -0.0096 1.0000 0.0540
-9.000 -0.5721 0.09844 0.09324 -0.0159 1.0000 0.0542
-8.500 -0.5496 0.09103 0.08591 -0.0097 1.0000 0.0566
-8.250 -0.5465 0.08726 0.08217 -0.0115 1.0000 0.0576
-8.000 -0.5465 0.08312 0.07805 -0.0146 1.0000 0.0585
-7.750 -0.5441 0.07893 0.07384 -0.0174 1.0000 0.0595
-7.500 -0.5408 0.07477 0.06964 -0.0199 1.0000 0.0606
-7.250 -0.5361 0.07068 0.06546 -0.0222 1.0000 0.0619
-7.000 -0.5358 0.06797 0.06216 -0.0261 1.0000 0.0661
-6.750 -0.5278 0.06498 0.05885 -0.0262 1.0000 0.0663
-6.500 -0.5147 0.05505 0.04872 -0.0261 1.0000 0.0442
-6.250 -0.5001 0.05186 0.04573 -0.0256 1.0000 0.0421
-6.000 -0.4877 0.04846 0.04216 -0.0249 1.0000 0.0406
-5.750 -0.4746 0.04496 0.03841 -0.0240 1.0000 0.0390
-5.500 -0.4602 0.04193 0.03511 -0.0228 1.0000 0.0388
-5.250 -0.4448 0.03940 0.03233 -0.0214 1.0000 0.0396
-5.000 -0.4288 0.03694 0.02959 -0.0199 1.0000 0.0402
-4.750 -0.4120 0.03447 0.02683 -0.0183 1.0000 0.0399
-4.500 -0.3945 0.03214 0.02418 -0.0167 1.0000 0.0395
-4.250 -0.3761 0.03004 0.02176 -0.0151 1.0000 0.0394
-4.000 -0.3568 0.02818 0.01961 -0.0136 1.0000 0.0395
-3.750 -0.3369 0.02659 0.01775 -0.0121 1.0000 0.0403
-3.500 -0.3162 0.02532 0.01618 -0.0107 1.0000 0.0421
-3.250 -0.2949 0.02417 0.01471 -0.0094 1.0000 0.0433
-3.000 -0.2589 0.02271 0.01298 -0.0109 0.9948 0.0441
-2.750 -0.2224 0.02110 0.01133 -0.0128 0.9883 0.0455
-2.500 -0.1859 0.02013 0.01036 -0.0148 0.9814 0.0487
-2.250 -0.1480 0.01919 0.00934 -0.0167 0.9751 0.0514
-2.000 -0.1125 0.01831 0.00841 -0.0181 0.9670 0.0532
-1.750 -0.0770 0.01739 0.00758 -0.0198 0.9595 0.0569
-1.500 -0.0424 0.01672 0.00698 -0.0212 0.9508 0.0611
-1.250 -0.0100 0.01619 0.00642 -0.0220 0.9403 0.0644
-1.000 0.0237 0.01566 0.00589 -0.0231 0.9306 0.0704
-0.750 0.0563 0.01529 0.00550 -0.0239 0.9193 0.0785
-0.500 0.0868 0.01490 0.00514 -0.0242 0.9068 0.0911
-0.250 0.1036 0.01240 0.00506 -0.0222 0.8949 0.7006
0.000 0.1532 0.01213 0.00532 -0.0235 0.8885 0.9454
0.250 0.2358 0.01203 0.00508 -0.0340 0.8820 1.0000
0.500 0.2614 0.01200 0.00495 -0.0334 0.8623 1.0000
0.750 0.2862 0.01197 0.00482 -0.0325 0.8413 1.0000
1.000 0.3100 0.01196 0.00471 -0.0313 0.8182 1.0000
1.250 0.3335 0.01197 0.00462 -0.0301 0.7940 1.0000
1.500 0.3568 0.01200 0.00456 -0.0288 0.7687 1.0000
1.750 0.3802 0.01205 0.00450 -0.0275 0.7435 1.0000
2.000 0.4033 0.01214 0.00449 -0.0263 0.7162 1.0000
2.250 0.4265 0.01224 0.00450 -0.0250 0.6879 1.0000
2.500 0.4495 0.01237 0.00453 -0.0238 0.6568 1.0000
2.750 0.4724 0.01253 0.00454 -0.0224 0.6225 1.0000
3.250 0.5177 0.01300 0.00467 -0.0199 0.5493 1.0000
3.500 0.5404 0.01330 0.00482 -0.0187 0.5128 1.0000
3.750 0.5629 0.01364 0.00499 -0.0175 0.4762 1.0000
4.000 0.5856 0.01399 0.00521 -0.0165 0.4358 1.0000
4.250 0.6080 0.01439 0.00546 -0.0154 0.3875 1.0000
4.500 0.6295 0.01490 0.00572 -0.0144 0.3282 1.0000
4.750 0.6504 0.01557 0.00607 -0.0133 0.2722 1.0000
5.000 0.6716 0.01629 0.00653 -0.0124 0.2251 1.0000
5.250 0.6932 0.01702 0.00708 -0.0115 0.1874 1.0000
5.500 0.7150 0.01773 0.00765 -0.0107 0.1593 1.0000
5.750 0.7367 0.01847 0.00826 -0.0099 0.1386 1.0000
6.000 0.7585 0.01920 0.00894 -0.0091 0.1233 1.0000
6.250 0.7800 0.01997 0.00964 -0.0083 0.1114 1.0000
6.500 0.8021 0.02069 0.01041 -0.0074 0.1019 1.0000
6.750 0.8234 0.02152 0.01124 -0.0066 0.0944 1.0000
7.000 0.8450 0.02232 0.01207 -0.0058 0.0874 1.0000
7.250 0.8660 0.02327 0.01304 -0.0049 0.0823 1.0000
7.500 0.8877 0.02418 0.01404 -0.0040 0.0775 1.0000
7.750 0.9085 0.02517 0.01501 -0.0033 0.0733 1.0000
8.000 0.9300 0.02624 0.01621 -0.0025 0.0694 1.0000
8.250 0.9514 0.02734 0.01743 -0.0017 0.0660 1.0000
8.500 0.9722 0.02845 0.01858 -0.0009 0.0630 1.0000
8.750 0.9923 0.02980 0.01996 -0.0002 0.0603 1.0000
9.000 1.0127 0.03112 0.02158 0.0006 0.0573 1.0000
9.250 1.0323 0.03254 0.02318 0.0015 0.0549 1.0000
9.500 1.0511 0.03382 0.02453 0.0022 0.0527 1.0000
9.750 1.0689 0.03544 0.02617 0.0030 0.0506 1.0000
10.000 1.0843 0.03738 0.02855 0.0042 0.0486 1.0000
10.250 1.0980 0.03946 0.03096 0.0053 0.0468 1.0000
10.500 1.1105 0.04131 0.03305 0.0065 0.0450 1.0000
10.750 1.1228 0.04289 0.03476 0.0075 0.0435 1.0000
11.000 1.1348 0.04467 0.03657 0.0085 0.0422 1.0000
11.250 1.1364 0.04763 0.03994 0.0101 0.0413 1.0000
11.500 1.1304 0.05098 0.04372 0.0121 0.0406 1.0000
11.750 1.1179 0.05445 0.04754 0.0141 0.0402 1.0000
12.000 1.1009 0.05842 0.05183 0.0150 0.0398 1.0000
12.250 1.0800 0.06322 0.05692 0.0144 0.0396 1.0000
12.500 1.0547 0.06929 0.06325 0.0119 0.0396 1.0000
12.750 1.0235 0.07736 0.07156 0.0067 0.0398 1.0000
13.000 0.9830 0.08893 0.08333 -0.0019 0.0403 1.0000
13.250 0.9246 0.10746 0.10198 -0.0148 0.0411 1.0000
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Polar data table (+)
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