GIII BL86 AIRFOIL (modified line 31) (giiid-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL86 AIRFOIL (modified line 31) (giiid-il) Reynolds number: 200,000 Max Cl/Cd: 59.25 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiid-il-200000.txt Download as CSV file: xf-giiid-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL86 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4839 0.11434 0.11109 -0.0045 1.0000 0.0501
-10.750 -0.4954 0.10948 0.10627 -0.0085 1.0000 0.0508
-10.500 -0.5041 0.10442 0.10124 -0.0118 1.0000 0.0510
-10.250 -0.5118 0.09901 0.09585 -0.0151 1.0000 0.0511
-10.000 -0.5153 0.09261 0.08950 -0.0143 1.0000 0.0522
-9.750 -0.5048 0.08999 0.08687 -0.0120 1.0000 0.0536
-9.500 -0.5036 0.08617 0.08306 -0.0123 1.0000 0.0548
-9.250 -0.5077 0.08152 0.07844 -0.0138 1.0000 0.0560
-9.000 -0.5162 0.07614 0.07308 -0.0164 1.0000 0.0570
-8.750 -0.5325 0.06951 0.06649 -0.0211 1.0000 0.0574
-8.500 -0.5548 0.06330 0.06025 -0.0252 1.0000 0.0572
-8.250 -0.5736 0.05849 0.05538 -0.0260 1.0000 0.0576
-8.000 -0.5859 0.05365 0.05045 -0.0261 1.0000 0.0588
-7.750 -0.5971 0.04856 0.04513 -0.0260 1.0000 0.0617
-7.500 -0.6177 0.04238 0.03841 -0.0243 1.0000 0.0647
-7.250 -0.6058 0.03818 0.03432 -0.0238 1.0000 0.0663
-7.000 -0.6543 0.03872 0.03347 -0.0165 1.0000 0.0412
-6.750 -0.6417 0.03356 0.02797 -0.0142 1.0000 0.0341
-6.500 -0.6294 0.02977 0.02368 -0.0117 1.0000 0.0336
-6.250 -0.6143 0.02758 0.02117 -0.0096 1.0000 0.0352
-6.000 -0.6010 0.02507 0.01827 -0.0068 1.0000 0.0352
-5.750 -0.5884 0.02310 0.01598 -0.0039 1.0000 0.0356
-5.500 -0.5747 0.02155 0.01417 -0.0013 1.0000 0.0365
-5.250 -0.5590 0.02045 0.01285 0.0009 1.0000 0.0381
-5.000 -0.5417 0.01898 0.01118 0.0027 1.0000 0.0408
-4.750 -0.5094 0.01751 0.00969 0.0015 0.9968 0.0444
-4.500 -0.4723 0.01643 0.00852 -0.0004 0.9926 0.0495
-4.250 -0.4375 0.01532 0.00744 -0.0022 0.9872 0.0596
-4.000 -0.4006 0.01425 0.00639 -0.0043 0.9828 0.0787
-3.750 -0.3682 0.01328 0.00571 -0.0058 0.9763 0.1320
-3.500 -0.3328 0.01237 0.00523 -0.0081 0.9712 0.2153
-3.250 -0.3041 0.01110 0.00475 -0.0093 0.9650 0.3818
-3.000 -0.2860 0.00971 0.00486 -0.0070 0.9578 0.7219
-2.750 -0.2555 0.00977 0.00507 -0.0064 0.9522 0.8119
-2.500 -0.2259 0.00996 0.00524 -0.0057 0.9451 0.8530
-2.250 -0.1915 0.01019 0.00540 -0.0059 0.9404 0.8798
-2.000 -0.1629 0.01043 0.00554 -0.0052 0.9323 0.8993
-1.750 -0.1271 0.01066 0.00567 -0.0059 0.9271 0.9140
-1.500 -0.0934 0.01087 0.00580 -0.0064 0.9199 0.9271
-1.250 -0.0501 0.01107 0.00589 -0.0088 0.9146 0.9367
-1.000 -0.0027 0.01122 0.00596 -0.0123 0.9096 0.9464
-0.750 0.0506 0.01140 0.00607 -0.0168 0.9043 0.9607
-0.500 0.0962 0.01142 0.00601 -0.0202 0.8982 0.9725
-0.250 0.1316 0.01135 0.00590 -0.0220 0.8888 0.9783
0.000 0.1637 0.01128 0.00578 -0.0230 0.8789 0.9838
0.250 0.1982 0.01114 0.00558 -0.0244 0.8665 0.9885
0.500 0.2301 0.01104 0.00542 -0.0252 0.8522 0.9941
0.750 0.2655 0.01087 0.00520 -0.0267 0.8380 0.9984
1.000 0.2917 0.01077 0.00507 -0.0266 0.8245 1.0000
1.250 0.3138 0.01070 0.00497 -0.0256 0.8126 1.0000
1.500 0.3369 0.01062 0.00489 -0.0248 0.8001 1.0000
1.750 0.3601 0.01055 0.00482 -0.0241 0.7875 1.0000
2.000 0.3835 0.01048 0.00477 -0.0233 0.7747 1.0000
2.250 0.4071 0.01041 0.00470 -0.0226 0.7617 1.0000
2.500 0.4307 0.01033 0.00464 -0.0218 0.7480 1.0000
2.750 0.4544 0.01025 0.00458 -0.0210 0.7336 1.0000
3.000 0.4782 0.01018 0.00454 -0.0202 0.7179 1.0000
3.250 0.5019 0.01012 0.00449 -0.0193 0.7011 1.0000
3.500 0.5256 0.01008 0.00448 -0.0184 0.6808 1.0000
3.750 0.5489 0.01007 0.00446 -0.0174 0.6588 1.0000
4.000 0.5721 0.01010 0.00451 -0.0164 0.6320 1.0000
4.250 0.5946 0.01018 0.00454 -0.0153 0.5962 1.0000
4.500 0.6156 0.01039 0.00457 -0.0138 0.5409 1.0000
4.750 0.6351 0.01081 0.00468 -0.0123 0.4608 1.0000
5.000 0.6527 0.01150 0.00493 -0.0107 0.3695 1.0000
5.250 0.6707 0.01222 0.00537 -0.0093 0.3104 1.0000
5.500 0.6898 0.01282 0.00579 -0.0081 0.2679 1.0000
5.750 0.7091 0.01336 0.00621 -0.0068 0.2282 1.0000
6.000 0.7274 0.01401 0.00666 -0.0055 0.1765 1.0000
6.250 0.7395 0.01550 0.00752 -0.0033 0.0821 1.0000
6.500 0.7527 0.01689 0.00874 -0.0010 0.0592 1.0000
6.750 0.7694 0.01782 0.00973 0.0008 0.0501 1.0000
7.000 0.7845 0.01904 0.01099 0.0029 0.0452 1.0000
7.250 0.8021 0.02010 0.01212 0.0047 0.0417 1.0000
7.500 0.8195 0.02138 0.01340 0.0062 0.0386 1.0000
7.750 0.8372 0.02334 0.01541 0.0077 0.0355 1.0000
8.000 0.8582 0.02468 0.01692 0.0090 0.0336 1.0000
8.250 0.8790 0.02642 0.01888 0.0102 0.0319 1.0000
8.500 0.8983 0.02788 0.02047 0.0113 0.0296 1.0000
8.750 0.9156 0.03030 0.02296 0.0123 0.0272 1.0000
9.000 0.9284 0.03484 0.02793 0.0139 0.0265 1.0000
9.250 0.9387 0.03817 0.03165 0.0158 0.0262 1.0000
9.500 0.9454 0.04252 0.03640 0.0177 0.0264 1.0000
9.750 0.9544 0.04513 0.03933 0.0195 0.0266 1.0000
10.000 0.9587 0.04811 0.04263 0.0215 0.0268 1.0000
10.250 0.9568 0.05169 0.04653 0.0235 0.0268 1.0000
10.500 0.9498 0.05541 0.05053 0.0254 0.0268 1.0000
10.750 0.9390 0.05863 0.05399 0.0276 0.0269 1.0000
11.000 0.9252 0.06151 0.05708 0.0293 0.0271 1.0000
11.250 0.7695 0.06072 0.05706 0.0336 0.0325 1.0000
11.500 0.7422 0.06716 0.06363 0.0310 0.0326 1.0000
11.750 0.7131 0.07485 0.07144 0.0270 0.0326 1.0000
12.000 0.6813 0.08439 0.08107 0.0214 0.0328 1.0000
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Polar data table (+)
Polar graphs
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