GIII BL369 AIRFOIL (giiik-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL369 AIRFOIL (giiik-il) Reynolds number: 500,000 Max Cl/Cd: 72.33 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiik-il-500000.txt Download as CSV file: xf-giiik-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL369 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4552 0.08145 0.07924 -0.0111 1.0000 0.0240
-8.750 -0.4643 0.07561 0.07341 -0.0148 1.0000 0.0246
-8.500 -0.4783 0.06877 0.06659 -0.0209 1.0000 0.0249
-8.250 -0.4948 0.06274 0.06053 -0.0264 1.0000 0.0249
-8.000 -0.5082 0.05735 0.05503 -0.0288 1.0000 0.0250
-7.750 -0.5138 0.05202 0.04956 -0.0300 1.0000 0.0251
-7.500 -0.5141 0.04729 0.04467 -0.0301 1.0000 0.0252
-7.250 -0.5124 0.04269 0.03989 -0.0297 1.0000 0.0252
-7.000 -0.5159 0.03626 0.03342 -0.0291 1.0000 0.0257
-6.750 -0.5082 0.03327 0.03040 -0.0280 1.0000 0.0260
-6.500 -0.5001 0.03077 0.02785 -0.0266 1.0000 0.0262
-6.250 -0.4927 0.02856 0.02558 -0.0247 1.0000 0.0266
-6.000 -0.4873 0.02656 0.02350 -0.0223 1.0000 0.0272
-5.750 -0.4828 0.02469 0.02153 -0.0195 0.9999 0.0279
-5.500 -0.4483 0.02198 0.01829 -0.0206 0.9964 0.0311
-5.250 -0.4265 0.01619 0.01200 -0.0219 0.9925 0.0318
-5.000 -0.3983 0.01354 0.00935 -0.0238 0.9887 0.0326
-4.750 -0.3662 0.01169 0.00739 -0.0257 0.9855 0.0337
-4.500 -0.3347 0.01008 0.00561 -0.0271 0.9821 0.0357
-4.250 -0.2972 0.01032 0.00548 -0.0278 0.9769 0.0390
-4.000 -0.3016 0.01866 0.01305 -0.0236 0.9831 0.0306
-3.750 -0.2694 0.01619 0.01033 -0.0244 0.9785 0.0298
-3.500 -0.2344 0.01463 0.00858 -0.0256 0.9749 0.0300
-3.250 -0.1985 0.01374 0.00755 -0.0270 0.9715 0.0309
-3.000 -0.1691 0.01238 0.00612 -0.0273 0.9637 0.0322
-2.750 -0.1368 0.01176 0.00555 -0.0283 0.9576 0.0344
-2.500 -0.1090 0.01123 0.00502 -0.0280 0.9476 0.0360
-2.250 -0.0809 0.01075 0.00451 -0.0279 0.9382 0.0375
-2.000 -0.0538 0.01052 0.00423 -0.0274 0.9275 0.0389
-1.750 -0.0304 0.00971 0.00342 -0.0264 0.9153 0.0416
-1.500 -0.0051 0.00938 0.00308 -0.0256 0.9034 0.0436
-1.250 0.0206 0.00913 0.00280 -0.0249 0.8913 0.0459
-1.000 0.0464 0.00896 0.00258 -0.0242 0.8781 0.0483
-0.750 0.0719 0.00867 0.00223 -0.0235 0.8640 0.0512
-0.500 0.0978 0.00847 0.00200 -0.0229 0.8495 0.0561
-0.250 0.1242 0.00832 0.00182 -0.0223 0.8349 0.0653
0.000 0.1335 0.00592 0.00164 -0.0194 0.8200 0.7386
0.250 0.1520 0.00561 0.00172 -0.0165 0.8043 0.8641
0.500 0.1750 0.00559 0.00176 -0.0147 0.7868 0.9113
0.750 0.2012 0.00566 0.00179 -0.0137 0.7672 0.9426
1.000 0.2340 0.00576 0.00183 -0.0142 0.7473 0.9626
1.250 0.2703 0.00589 0.00186 -0.0157 0.7271 0.9755
1.500 0.3139 0.00603 0.00189 -0.0188 0.6987 0.9860
1.750 0.3538 0.00618 0.00187 -0.0214 0.6598 0.9921
2.000 0.3902 0.00631 0.00185 -0.0233 0.6224 0.9962
2.250 0.4268 0.00648 0.00185 -0.0253 0.5832 1.0000
2.500 0.4512 0.00664 0.00187 -0.0248 0.5501 1.0000
2.750 0.4752 0.00683 0.00192 -0.0241 0.5159 1.0000
3.000 0.4989 0.00707 0.00199 -0.0234 0.4799 1.0000
3.250 0.5225 0.00731 0.00208 -0.0227 0.4435 1.0000
3.500 0.5461 0.00755 0.00218 -0.0220 0.4037 1.0000
3.750 0.5691 0.00789 0.00230 -0.0212 0.3522 1.0000
4.000 0.5915 0.00832 0.00248 -0.0203 0.2971 1.0000
4.250 0.6139 0.00878 0.00271 -0.0195 0.2447 1.0000
4.500 0.6361 0.00926 0.00296 -0.0186 0.1958 1.0000
4.750 0.6586 0.00973 0.00324 -0.0178 0.1553 1.0000
5.000 0.6812 0.01020 0.00353 -0.0169 0.1229 1.0000
5.250 0.7044 0.01062 0.00385 -0.0162 0.1008 1.0000
5.500 0.7279 0.01104 0.00419 -0.0155 0.0858 1.0000
5.750 0.7515 0.01147 0.00457 -0.0147 0.0747 1.0000
6.000 0.7748 0.01197 0.00503 -0.0140 0.0658 1.0000
6.250 0.7993 0.01231 0.00539 -0.0134 0.0607 1.0000
6.500 0.8216 0.01297 0.00602 -0.0126 0.0554 1.0000
6.750 0.8465 0.01328 0.00637 -0.0121 0.0528 1.0000
7.000 0.8709 0.01366 0.00678 -0.0116 0.0499 1.0000
7.250 0.8934 0.01431 0.00742 -0.0109 0.0467 1.0000
7.500 0.9164 0.01490 0.00807 -0.0102 0.0448 1.0000
7.750 0.9406 0.01531 0.00854 -0.0096 0.0428 1.0000
8.000 0.9645 0.01575 0.00900 -0.0091 0.0407 1.0000
8.250 0.9868 0.01642 0.00967 -0.0085 0.0386 1.0000
8.500 1.0070 0.01743 0.01075 -0.0075 0.0369 1.0000
8.750 1.0306 0.01791 0.01132 -0.0069 0.0355 1.0000
9.000 1.0537 0.01843 0.01190 -0.0064 0.0337 1.0000
9.250 1.0763 0.01898 0.01247 -0.0058 0.0321 1.0000
9.500 1.0930 0.02055 0.01408 -0.0046 0.0302 1.0000
9.750 1.1157 0.02107 0.01472 -0.0039 0.0293 1.0000
10.000 1.1370 0.02179 0.01555 -0.0032 0.0281 1.0000
10.250 1.1577 0.02254 0.01637 -0.0024 0.0269 1.0000
10.500 1.1777 0.02330 0.01716 -0.0016 0.0259 1.0000
10.750 1.1928 0.02494 0.01887 -0.0004 0.0247 1.0000
11.000 1.2102 0.02609 0.02019 0.0006 0.0240 1.0000
11.250 1.2279 0.02704 0.02129 0.0017 0.0232 1.0000
11.500 1.2438 0.02816 0.02255 0.0028 0.0225 1.0000
11.750 1.2586 0.02930 0.02381 0.0041 0.0218 1.0000
12.000 1.2723 0.03040 0.02502 0.0053 0.0212 1.0000
12.250 1.2835 0.03154 0.02623 0.0069 0.0207 1.0000
12.500 1.2906 0.03302 0.02779 0.0087 0.0203 1.0000
12.750 1.2870 0.03596 0.03092 0.0111 0.0198 1.0000
13.000 1.2865 0.03801 0.03318 0.0129 0.0195 1.0000
13.250 1.2869 0.03996 0.03532 0.0142 0.0192 1.0000
13.500 1.2846 0.04242 0.03798 0.0150 0.0189 1.0000
13.750 1.2796 0.04541 0.04117 0.0153 0.0186 1.0000
14.000 1.2720 0.04898 0.04495 0.0149 0.0184 1.0000
14.250 1.2614 0.05322 0.04939 0.0136 0.0182 1.0000
14.500 1.2480 0.05825 0.05462 0.0115 0.0181 1.0000
14.750 1.2312 0.06425 0.06082 0.0083 0.0180 1.0000
15.000 1.2095 0.07160 0.06838 0.0039 0.0180 1.0000
15.250 1.1812 0.08073 0.07771 -0.0020 0.0181 1.0000
15.500 1.1432 0.09247 0.08969 -0.0096 0.0183 1.0000
15.750 1.0882 0.10925 0.10670 -0.0202 0.0188 1.0000
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Polar data table (+)
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