GIII BL369 AIRFOIL (giiik-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL369 AIRFOIL (giiik-il) Reynolds number: 500,000 Max Cl/Cd: 66.35 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiik-il-500000-n5.txt Download as CSV file: xf-giiik-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6000 0.08192 0.07957 -0.0089 1.0000 0.0129
-8.750 -0.6076 0.07552 0.07319 -0.0162 1.0000 0.0128
-8.500 -0.6124 0.06958 0.06718 -0.0209 1.0000 0.0128
-8.250 -0.6137 0.06369 0.06118 -0.0243 1.0000 0.0128
-8.000 -0.6144 0.05709 0.05440 -0.0266 1.0000 0.0129
-7.750 -0.6134 0.05012 0.04719 -0.0277 1.0000 0.0131
-7.500 -0.6084 0.04444 0.04126 -0.0275 1.0000 0.0131
-7.250 -0.6060 0.03741 0.03383 -0.0261 1.0000 0.0131
-7.000 -0.6055 0.03010 0.02597 -0.0234 1.0000 0.0134
-6.750 -0.5918 0.02764 0.02329 -0.0216 1.0000 0.0136
-6.500 -0.5770 0.02553 0.02095 -0.0198 1.0000 0.0138
-6.250 -0.5495 0.02277 0.01787 -0.0205 0.9963 0.0141
-6.000 -0.5211 0.01985 0.01455 -0.0212 0.9920 0.0145
-5.750 -0.4910 0.01745 0.01179 -0.0221 0.9876 0.0151
-5.500 -0.4602 0.01581 0.00986 -0.0228 0.9822 0.0160
-5.250 -0.4285 0.01457 0.00839 -0.0237 0.9764 0.0166
-5.000 -0.3981 0.01374 0.00749 -0.0244 0.9687 0.0171
-4.750 -0.3665 0.01329 0.00702 -0.0253 0.9610 0.0175
-4.500 -0.3358 0.01284 0.00653 -0.0259 0.9510 0.0182
-4.250 -0.3072 0.01235 0.00597 -0.0260 0.9391 0.0190
-4.000 -0.2796 0.01185 0.00539 -0.0259 0.9279 0.0200
-3.750 -0.2526 0.01145 0.00491 -0.0256 0.9174 0.0208
-3.500 -0.2267 0.01103 0.00447 -0.0252 0.9059 0.0218
-3.250 -0.2002 0.01080 0.00423 -0.0248 0.8943 0.0228
-3.000 -0.1738 0.01060 0.00399 -0.0244 0.8828 0.0242
-2.750 -0.1473 0.01041 0.00373 -0.0239 0.8715 0.0255
-2.500 -0.1214 0.01009 0.00337 -0.0235 0.8592 0.0267
-2.250 -0.0954 0.00980 0.00307 -0.0230 0.8470 0.0283
-2.000 -0.0689 0.00960 0.00284 -0.0226 0.8350 0.0296
-1.750 -0.0425 0.00940 0.00259 -0.0222 0.8225 0.0308
-1.500 -0.0158 0.00925 0.00240 -0.0219 0.8095 0.0323
-1.250 0.0110 0.00913 0.00222 -0.0215 0.7958 0.0332
-1.000 0.0373 0.00892 0.00195 -0.0211 0.7800 0.0349
-0.750 0.0638 0.00881 0.00178 -0.0207 0.7627 0.0369
-0.500 0.0905 0.00873 0.00165 -0.0203 0.7457 0.0393
-0.250 0.1175 0.00868 0.00155 -0.0200 0.7289 0.0423
0.000 0.1443 0.00862 0.00146 -0.0197 0.7108 0.0490
0.250 0.1707 0.00851 0.00138 -0.0193 0.6893 0.0806
0.500 0.1826 0.00642 0.00127 -0.0170 0.6653 0.7195
0.750 0.2054 0.00631 0.00130 -0.0156 0.6327 0.7956
1.000 0.2288 0.00630 0.00134 -0.0143 0.6019 0.8465
1.250 0.2531 0.00635 0.00140 -0.0132 0.5748 0.8851
1.500 0.2787 0.00648 0.00146 -0.0125 0.5418 0.9136
1.750 0.3069 0.00671 0.00155 -0.0123 0.5010 0.9413
2.000 0.3389 0.00693 0.00164 -0.0131 0.4685 0.9605
2.250 0.3714 0.00712 0.00171 -0.0142 0.4411 0.9693
2.500 0.4030 0.00729 0.00178 -0.0150 0.4145 0.9765
2.750 0.4353 0.00753 0.00187 -0.0161 0.3746 0.9824
3.000 0.4667 0.00791 0.00199 -0.0172 0.3186 0.9878
3.250 0.4982 0.00840 0.00217 -0.0183 0.2506 0.9926
3.500 0.5302 0.00882 0.00236 -0.0196 0.2027 0.9968
3.750 0.5612 0.00916 0.00255 -0.0205 0.1701 1.0000
4.000 0.5846 0.00945 0.00273 -0.0198 0.1456 1.0000
4.250 0.6080 0.00977 0.00293 -0.0190 0.1219 1.0000
4.500 0.6314 0.01009 0.00314 -0.0183 0.1016 1.0000
4.750 0.6551 0.01039 0.00337 -0.0176 0.0880 1.0000
5.000 0.6793 0.01066 0.00360 -0.0169 0.0786 1.0000
5.250 0.7035 0.01095 0.00385 -0.0163 0.0702 1.0000
5.500 0.7280 0.01123 0.00411 -0.0157 0.0630 1.0000
5.750 0.7525 0.01152 0.00438 -0.0152 0.0570 1.0000
6.000 0.7770 0.01184 0.00468 -0.0147 0.0513 1.0000
6.250 0.8017 0.01216 0.00500 -0.0142 0.0472 1.0000
6.500 0.8264 0.01248 0.00532 -0.0137 0.0441 1.0000
6.750 0.8507 0.01286 0.00570 -0.0132 0.0413 1.0000
7.000 0.8751 0.01324 0.00611 -0.0127 0.0392 1.0000
7.250 0.8999 0.01357 0.00647 -0.0122 0.0373 1.0000
7.500 0.9243 0.01393 0.00685 -0.0118 0.0352 1.0000
7.750 0.9483 0.01437 0.00729 -0.0113 0.0333 1.0000
8.000 0.9718 0.01487 0.00783 -0.0107 0.0317 1.0000
8.250 0.9961 0.01525 0.00826 -0.0103 0.0306 1.0000
8.500 1.0200 0.01567 0.00874 -0.0098 0.0295 1.0000
8.750 1.0437 0.01611 0.00924 -0.0093 0.0283 1.0000
9.000 1.0670 0.01660 0.00976 -0.0088 0.0271 1.0000
9.250 1.0891 0.01723 0.01042 -0.0081 0.0258 1.0000
9.500 1.1114 0.01783 0.01109 -0.0075 0.0249 1.0000
9.750 1.1342 0.01833 0.01168 -0.0069 0.0241 1.0000
10.000 1.1567 0.01885 0.01227 -0.0064 0.0230 1.0000
10.250 1.1790 0.01937 0.01284 -0.0058 0.0219 1.0000
10.500 1.2004 0.01997 0.01348 -0.0052 0.0209 1.0000
10.750 1.2197 0.02080 0.01437 -0.0043 0.0200 1.0000
11.000 1.2403 0.02146 0.01514 -0.0035 0.0194 1.0000
11.250 1.2600 0.02218 0.01596 -0.0027 0.0187 1.0000
11.500 1.2790 0.02292 0.01679 -0.0018 0.0180 1.0000
11.750 1.2978 0.02365 0.01760 -0.0009 0.0174 1.0000
12.000 1.3156 0.02442 0.01843 0.0000 0.0167 1.0000
12.250 1.3308 0.02538 0.01945 0.0012 0.0161 1.0000
12.500 1.3441 0.02643 0.02062 0.0026 0.0157 1.0000
12.750 1.3556 0.02745 0.02177 0.0043 0.0154 1.0000
13.000 1.3652 0.02859 0.02303 0.0060 0.0150 1.0000
13.250 1.3734 0.02985 0.02441 0.0076 0.0147 1.0000
13.500 1.3804 0.03123 0.02593 0.0091 0.0144 1.0000
13.750 1.3868 0.03274 0.02756 0.0103 0.0140 1.0000
14.000 1.3922 0.03442 0.02935 0.0112 0.0137 1.0000
14.250 1.3968 0.03629 0.03134 0.0118 0.0135 1.0000
14.500 1.3993 0.03849 0.03365 0.0121 0.0132 1.0000
14.750 1.3993 0.04113 0.03640 0.0120 0.0130 1.0000
15.000 1.3960 0.04436 0.03976 0.0114 0.0128 1.0000
15.250 1.3887 0.04834 0.04388 0.0102 0.0126 1.0000
15.500 1.3807 0.05275 0.04844 0.0084 0.0124 1.0000
15.750 1.3713 0.05764 0.05350 0.0060 0.0124 1.0000
16.000 1.3588 0.06327 0.05931 0.0031 0.0123 1.0000
16.250 1.3429 0.06971 0.06592 -0.0004 0.0123 1.0000
16.500 1.3229 0.07699 0.07337 -0.0044 0.0122 1.0000
16.750 1.2994 0.08518 0.08173 -0.0088 0.0122 1.0000
17.000 1.2725 0.09430 0.09100 -0.0138 0.0122 1.0000
17.250 1.2429 0.10422 0.10108 -0.0192 0.0123 1.0000
17.500 1.2114 0.11477 0.11177 -0.0248 0.0123 1.0000
17.750 1.1785 0.12601 0.12314 -0.0309 0.0124 1.0000
18.000 1.1443 0.13791 0.13518 -0.0373 0.0124 1.0000
18.250 1.1060 0.15157 0.14897 -0.0449 0.0125 1.0000
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Polar data table (+)
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