GIII BL126 AIRFOIL (giiie-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL126 AIRFOIL (giiie-il) Reynolds number: 200,000 Max Cl/Cd: 55.83 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiie-il-200000-n5.txt Download as CSV file: xf-giiie-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6165 0.08386 0.08058 -0.0102 1.0000 0.0118
-9.000 -0.6218 0.07703 0.07377 -0.0168 1.0000 0.0117
-8.750 -0.6295 0.07126 0.06797 -0.0209 1.0000 0.0116
-8.500 -0.6365 0.06548 0.06210 -0.0233 1.0000 0.0116
-8.250 -0.6415 0.05931 0.05578 -0.0248 1.0000 0.0116
-8.000 -0.6441 0.05290 0.04915 -0.0254 1.0000 0.0117
-7.750 -0.6438 0.04659 0.04253 -0.0249 1.0000 0.0116
-7.500 -0.6415 0.04102 0.03654 -0.0238 1.0000 0.0116
-7.250 -0.6375 0.03568 0.03069 -0.0221 1.0000 0.0117
-7.000 -0.6299 0.03108 0.02555 -0.0201 1.0000 0.0119
-6.750 -0.6168 0.02786 0.02190 -0.0184 1.0000 0.0123
-6.500 -0.6000 0.02566 0.01939 -0.0169 1.0000 0.0129
-6.250 -0.5817 0.02383 0.01727 -0.0155 1.0000 0.0136
-6.000 -0.5625 0.02251 0.01568 -0.0142 1.0000 0.0148
-5.750 -0.5428 0.02140 0.01435 -0.0128 0.9998 0.0165
-5.500 -0.5093 0.01965 0.01226 -0.0141 0.9915 0.0178
-5.250 -0.4767 0.01802 0.01037 -0.0153 0.9824 0.0189
-5.000 -0.4455 0.01653 0.00878 -0.0164 0.9722 0.0214
-4.750 -0.4131 0.01579 0.00796 -0.0176 0.9617 0.0247
-4.500 -0.3814 0.01490 0.00690 -0.0185 0.9511 0.0272
-4.250 -0.3518 0.01407 0.00596 -0.0190 0.9394 0.0306
-4.000 -0.3221 0.01351 0.00536 -0.0195 0.9281 0.0382
-3.750 -0.2936 0.01296 0.00480 -0.0198 0.9170 0.0505
-3.500 -0.2658 0.01251 0.00438 -0.0199 0.9066 0.0696
-3.250 -0.2387 0.01214 0.00405 -0.0199 0.8968 0.0968
-3.000 -0.2127 0.01179 0.00377 -0.0197 0.8870 0.1277
-2.500 -0.1626 0.01096 0.00324 -0.0189 0.8696 0.2290
-2.250 -0.1459 0.00968 0.00287 -0.0174 0.8608 0.4609
-2.000 -0.1303 0.00889 0.00297 -0.0144 0.8537 0.7095
-1.750 -0.1062 0.00881 0.00299 -0.0132 0.8461 0.7699
-1.500 -0.0810 0.00879 0.00297 -0.0121 0.8399 0.8052
-1.250 -0.0554 0.00880 0.00297 -0.0113 0.8328 0.8324
-1.000 -0.0294 0.00883 0.00295 -0.0105 0.8270 0.8552
-0.750 -0.0027 0.00888 0.00298 -0.0099 0.8204 0.8752
-0.500 0.0241 0.00895 0.00304 -0.0092 0.8143 0.8975
-0.250 0.0535 0.00907 0.00313 -0.0089 0.8087 0.9200
0.000 0.0846 0.00915 0.00317 -0.0093 0.8024 0.9319
0.250 0.1140 0.00918 0.00313 -0.0097 0.7958 0.9385
0.500 0.1458 0.00920 0.00312 -0.0105 0.7866 0.9435
0.750 0.1747 0.00922 0.00309 -0.0107 0.7760 0.9506
1.000 0.2076 0.00924 0.00307 -0.0117 0.7652 0.9551
1.250 0.2388 0.00926 0.00305 -0.0125 0.7544 0.9610
1.500 0.2708 0.00927 0.00307 -0.0134 0.7437 0.9664
1.750 0.3041 0.00929 0.00311 -0.0147 0.7333 0.9715
2.000 0.3367 0.00930 0.00314 -0.0158 0.7228 0.9770
2.250 0.3711 0.00931 0.00319 -0.0173 0.7114 0.9814
2.500 0.4043 0.00932 0.00324 -0.0185 0.6987 0.9867
2.750 0.4387 0.00933 0.00329 -0.0201 0.6838 0.9912
3.000 0.4724 0.00934 0.00334 -0.0214 0.6645 0.9962
3.250 0.5035 0.00938 0.00333 -0.0221 0.6301 1.0000
3.500 0.5252 0.00953 0.00333 -0.0208 0.5801 1.0000
3.750 0.5466 0.00979 0.00340 -0.0196 0.5228 1.0000
4.000 0.5653 0.01035 0.00354 -0.0181 0.4235 1.0000
4.250 0.5829 0.01112 0.00391 -0.0166 0.3345 1.0000
4.500 0.6015 0.01184 0.00429 -0.0153 0.2572 1.0000
4.750 0.6196 0.01266 0.00472 -0.0141 0.1746 1.0000
5.000 0.6370 0.01360 0.00525 -0.0127 0.0986 1.0000
5.250 0.6562 0.01436 0.00582 -0.0115 0.0622 1.0000
5.500 0.6768 0.01500 0.00643 -0.0104 0.0461 1.0000
5.750 0.6969 0.01574 0.00721 -0.0092 0.0366 1.0000
6.000 0.7185 0.01630 0.00787 -0.0082 0.0310 1.0000
6.250 0.7382 0.01715 0.00875 -0.0070 0.0269 1.0000
6.500 0.7578 0.01807 0.00979 -0.0057 0.0248 1.0000
6.750 0.7788 0.01883 0.01066 -0.0047 0.0221 1.0000
7.000 0.7996 0.01963 0.01152 -0.0038 0.0195 1.0000
7.250 0.8184 0.02083 0.01280 -0.0026 0.0178 1.0000
7.500 0.8352 0.02283 0.01495 -0.0011 0.0164 1.0000
7.750 0.8568 0.02384 0.01615 -0.0002 0.0152 1.0000
8.000 0.8777 0.02492 0.01741 0.0007 0.0135 1.0000
8.250 0.8973 0.02646 0.01914 0.0017 0.0125 1.0000
8.500 0.9159 0.02810 0.02099 0.0028 0.0118 1.0000
8.750 0.9330 0.02992 0.02301 0.0039 0.0112 1.0000
9.000 0.9472 0.03229 0.02564 0.0052 0.0107 1.0000
9.250 0.9553 0.03587 0.02962 0.0070 0.0103 1.0000
9.500 0.9601 0.03935 0.03353 0.0089 0.0100 1.0000
9.750 0.9657 0.04199 0.03658 0.0108 0.0095 1.0000
10.000 0.9653 0.04519 0.04018 0.0128 0.0091 1.0000
10.250 0.9577 0.04860 0.04393 0.0150 0.0087 1.0000
10.500 0.9443 0.05224 0.04784 0.0169 0.0085 1.0000
10.750 0.9278 0.05647 0.05233 0.0173 0.0085 1.0000
11.000 0.9090 0.06151 0.05758 0.0161 0.0085 1.0000
11.250 0.8887 0.06754 0.06381 0.0131 0.0086 1.0000
11.500 0.8672 0.07500 0.07144 0.0080 0.0088 1.0000
11.750 0.8453 0.08446 0.08101 0.0007 0.0092 1.0000
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Polar data table (+)
Polar graphs
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