GIII BL387 AIRFOIL (giiil-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL387 AIRFOIL (giiil-il) Reynolds number: 100,000 Max Cl/Cd: 45.02 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiil-il-100000.txt Download as CSV file: xf-giiil-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5472 0.09527 0.09021 -0.0054 1.0000 0.0877
-8.250 -0.5609 0.09075 0.08573 -0.0144 1.0000 0.0893
-8.000 -0.5772 0.08780 0.08253 -0.0219 1.0000 0.0903
-7.750 -0.5547 0.08151 0.07652 -0.0172 1.0000 0.0932
-7.500 -0.5439 0.07835 0.07340 -0.0162 1.0000 0.0967
-7.250 -0.5397 0.07456 0.06955 -0.0186 1.0000 0.1010
-7.000 -0.5489 0.07138 0.06590 -0.0249 1.0000 0.1064
-6.750 -0.5314 0.06626 0.06106 -0.0229 1.0000 0.1092
-6.500 -0.5193 0.06321 0.05801 -0.0224 1.0000 0.1143
-6.250 -0.5149 0.05983 0.05429 -0.0245 1.0000 0.1231
-6.000 -0.5000 0.05645 0.05106 -0.0232 1.0000 0.1279
-5.750 -0.4912 0.05356 0.04791 -0.0235 1.0000 0.1397
-5.500 -0.4769 0.05089 0.04530 -0.0224 1.0000 0.1487
-5.250 -0.4659 0.04795 0.04230 -0.0214 1.0000 0.1604
-5.000 -0.4547 0.04549 0.03979 -0.0201 1.0000 0.1769
-4.750 -0.4458 0.04336 0.03757 -0.0187 1.0000 0.2038
-4.000 -0.4173 0.03699 0.03148 -0.0114 1.0000 0.2993
-3.750 -0.4072 0.03496 0.02961 -0.0083 1.0000 0.3338
-3.500 -0.3962 0.03306 0.02779 -0.0054 1.0000 0.3685
-3.000 -0.2940 0.02654 0.01822 -0.0102 1.0000 0.1155
-2.750 -0.2684 0.02494 0.01617 -0.0086 1.0000 0.1025
-2.500 -0.2437 0.02313 0.01408 -0.0075 1.0000 0.0956
-2.250 -0.2191 0.02240 0.01295 -0.0061 1.0000 0.0913
-2.000 -0.1949 0.02098 0.01148 -0.0055 1.0000 0.0927
-1.750 -0.1708 0.01995 0.01046 -0.0050 1.0000 0.0951
-1.500 -0.1460 0.01911 0.00958 -0.0044 1.0000 0.0960
-1.250 -0.1215 0.01841 0.00892 -0.0039 1.0000 0.0983
-1.000 -0.0982 0.01794 0.00848 -0.0034 1.0000 0.1036
-0.750 -0.0751 0.01735 0.00797 -0.0029 1.0000 0.1078
-0.500 -0.0456 0.01688 0.00760 -0.0038 0.9975 0.1152
0.000 0.0535 0.01356 0.00723 -0.0104 0.9857 1.0000
0.250 0.1087 0.01382 0.00718 -0.0161 0.9734 1.0000
0.500 0.1638 0.01399 0.00721 -0.0218 0.9601 1.0000
0.750 0.2223 0.01404 0.00720 -0.0279 0.9460 1.0000
1.000 0.2813 0.01394 0.00708 -0.0338 0.9303 1.0000
1.250 0.3333 0.01375 0.00689 -0.0378 0.9124 1.0000
1.500 0.3710 0.01359 0.00673 -0.0388 0.8900 1.0000
1.750 0.4014 0.01345 0.00657 -0.0383 0.8664 1.0000
2.000 0.4263 0.01337 0.00646 -0.0366 0.8417 1.0000
2.250 0.4495 0.01329 0.00634 -0.0346 0.8169 1.0000
2.500 0.4707 0.01328 0.00628 -0.0323 0.7893 1.0000
2.750 0.4921 0.01326 0.00620 -0.0300 0.7610 1.0000
3.000 0.5136 0.01327 0.00612 -0.0278 0.7315 1.0000
3.250 0.5354 0.01332 0.00610 -0.0258 0.7006 1.0000
3.500 0.5572 0.01340 0.00610 -0.0239 0.6676 1.0000
3.750 0.5792 0.01351 0.00611 -0.0221 0.6323 1.0000
4.000 0.6011 0.01368 0.00615 -0.0202 0.5947 1.0000
4.250 0.6225 0.01393 0.00626 -0.0185 0.5509 1.0000
4.500 0.6433 0.01429 0.00642 -0.0167 0.5014 1.0000
4.750 0.6629 0.01477 0.00665 -0.0148 0.4384 1.0000
5.000 0.6809 0.01546 0.00696 -0.0129 0.3490 1.0000
5.250 0.6972 0.01671 0.00758 -0.0111 0.2672 1.0000
5.500 0.7158 0.01798 0.00845 -0.0097 0.2181 1.0000
5.750 0.7362 0.01913 0.00936 -0.0085 0.1882 1.0000
6.000 0.7578 0.02023 0.01029 -0.0075 0.1676 1.0000
6.250 0.7804 0.02140 0.01132 -0.0067 0.1523 1.0000
6.500 0.8038 0.02253 0.01245 -0.0059 0.1398 1.0000
6.750 0.8275 0.02382 0.01376 -0.0052 0.1298 1.0000
7.000 0.8521 0.02547 0.01524 -0.0048 0.1221 1.0000
7.250 0.8755 0.02665 0.01672 -0.0040 0.1149 1.0000
7.500 0.8996 0.02833 0.01829 -0.0036 0.1089 1.0000
7.750 0.9220 0.03016 0.02049 -0.0027 0.1045 1.0000
8.000 0.9440 0.03174 0.02230 -0.0018 0.0993 1.0000
8.250 0.9661 0.03396 0.02451 -0.0014 0.0953 1.0000
8.500 0.9831 0.03650 0.02755 -0.0001 0.0926 1.0000
8.750 0.9983 0.03892 0.03048 0.0014 0.0892 1.0000
9.000 1.0132 0.04156 0.03348 0.0026 0.0866 1.0000
9.250 1.0285 0.04429 0.03643 0.0036 0.0845 1.0000
9.500 1.0435 0.04791 0.04007 0.0040 0.0820 1.0000
9.750 1.0443 0.05185 0.04456 0.0058 0.0809 1.0000
10.000 1.0416 0.05616 0.04936 0.0075 0.0804 1.0000
10.250 1.0370 0.06102 0.05457 0.0087 0.0807 1.0000
10.500 1.0319 0.06626 0.06004 0.0095 0.0813 1.0000
10.750 0.8533 0.09582 0.09051 -0.0087 0.1110 1.0000
11.000 0.8662 0.09756 0.09227 -0.0063 0.1095 1.0000
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Polar data table (+)
Polar graphs
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