GIII BL0 AIRFOIL (giiia-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GIII BL0 AIRFOIL (giiia-il) Reynolds number: 50,000 Max Cl/Cd: 26.4 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiia-il-50000.txt Download as CSV file: xf-giiia-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL0 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5390 0.09891 0.09211 0.0150 1.0000 0.3786
-8.500 -0.5345 0.09528 0.08852 0.0156 1.0000 0.3942
-8.250 -0.6910 0.07816 0.07159 -0.0134 1.0000 0.2112
-7.750 -0.7110 0.06098 0.05359 -0.0154 1.0000 0.1349
-7.500 -0.7170 0.05599 0.04816 -0.0128 1.0000 0.1277
-7.250 -0.7163 0.05198 0.04359 -0.0097 1.0000 0.1231
-7.000 -0.7090 0.04829 0.03954 -0.0071 1.0000 0.1221
-6.750 -0.7028 0.04512 0.03586 -0.0039 1.0000 0.1232
-6.500 -0.6938 0.04210 0.03235 -0.0009 1.0000 0.1256
-6.250 -0.6765 0.03921 0.02938 0.0009 1.0000 0.1293
-6.000 -0.6595 0.03656 0.02636 0.0031 1.0000 0.1332
-5.750 -0.6422 0.03422 0.02362 0.0053 1.0000 0.1413
-5.500 -0.6209 0.03213 0.02127 0.0069 1.0000 0.1513
-5.250 -0.5979 0.03011 0.01908 0.0083 1.0000 0.1659
-5.000 -0.5711 0.02805 0.01708 0.0090 1.0000 0.1869
-4.750 -0.5438 0.02614 0.01528 0.0097 1.0000 0.2230
-4.500 -0.5137 0.02368 0.01333 0.0099 1.0000 0.2924
-4.250 -0.5020 0.02060 0.01168 0.0130 1.0000 0.4304
-4.000 -0.2167 0.02666 0.01742 -0.0119 1.0000 0.9596
-3.750 -0.1130 0.02493 0.01504 -0.0274 1.0000 1.0000
-3.500 -0.0962 0.02430 0.01426 -0.0270 1.0000 1.0000
-3.250 -0.0795 0.02373 0.01356 -0.0265 1.0000 1.0000
-3.000 -0.0631 0.02322 0.01294 -0.0259 1.0000 1.0000
-2.750 -0.0471 0.02276 0.01237 -0.0251 1.0000 1.0000
-2.500 -0.0319 0.02236 0.01189 -0.0242 1.0000 1.0000
-2.250 -0.0177 0.02200 0.01147 -0.0230 1.0000 1.0000
-2.000 -0.0048 0.02169 0.01112 -0.0215 1.0000 1.0000
-1.750 0.0063 0.02143 0.01084 -0.0197 1.0000 1.0000
-1.500 0.0151 0.02123 0.01062 -0.0175 1.0000 1.0000
-1.250 0.0218 0.02109 0.01047 -0.0149 1.0000 1.0000
-1.000 0.0265 0.02099 0.01037 -0.0119 1.0000 1.0000
-0.750 0.0294 0.02095 0.01033 -0.0087 1.0000 1.0000
-0.500 0.0306 0.02097 0.01034 -0.0052 1.0000 1.0000
-0.250 0.0307 0.02103 0.01041 -0.0015 1.0000 1.0000
0.000 0.0299 0.02117 0.01053 0.0023 1.0000 1.0000
0.250 0.0284 0.02137 0.01073 0.0060 1.0000 1.0000
0.500 0.0265 0.02166 0.01101 0.0096 1.0000 1.0000
0.750 0.0247 0.02203 0.01137 0.0131 1.0000 1.0000
1.000 0.0238 0.02249 0.01181 0.0162 1.0000 1.0000
1.250 0.0245 0.02301 0.01231 0.0189 1.0000 1.0000
1.500 0.0270 0.02359 0.01287 0.0212 1.0000 1.0000
1.750 0.1129 0.02469 0.01410 0.0082 0.9742 1.0000
2.000 0.2487 0.02487 0.01458 -0.0117 0.9295 1.0000
2.250 0.3436 0.02451 0.01453 -0.0236 0.8992 1.0000
2.500 0.4161 0.02378 0.01407 -0.0303 0.8672 1.0000
2.750 0.4598 0.02316 0.01365 -0.0313 0.8301 1.0000
3.000 0.4950 0.02243 0.01304 -0.0301 0.7907 1.0000
3.250 0.5185 0.02185 0.01251 -0.0268 0.7437 1.0000
3.500 0.5408 0.02129 0.01182 -0.0227 0.6878 1.0000
3.750 0.5608 0.02136 0.01158 -0.0188 0.6185 1.0000
4.000 0.5805 0.02203 0.01189 -0.0160 0.5530 1.0000
4.250 0.6019 0.02287 0.01250 -0.0142 0.5083 1.0000
4.500 0.6238 0.02370 0.01322 -0.0129 0.4774 1.0000
4.750 0.6466 0.02449 0.01393 -0.0118 0.4552 1.0000
5.000 0.6683 0.02539 0.01493 -0.0108 0.4367 1.0000
5.250 0.6909 0.02635 0.01597 -0.0099 0.4232 1.0000
5.500 0.7137 0.02734 0.01703 -0.0090 0.4117 1.0000
5.750 0.7341 0.02848 0.01843 -0.0080 0.4005 1.0000
6.000 0.7543 0.02970 0.01985 -0.0070 0.3908 1.0000
6.250 0.7765 0.03090 0.02117 -0.0061 0.3831 1.0000
6.500 0.7928 0.03250 0.02315 -0.0048 0.3747 1.0000
6.750 0.8131 0.03382 0.02461 -0.0036 0.3663 1.0000
7.000 0.8279 0.03552 0.02669 -0.0020 0.3572 1.0000
7.250 0.8429 0.03693 0.02834 -0.0001 0.3443 1.0000
7.500 0.8612 0.03670 0.02805 0.0025 0.3167 1.0000
7.750 0.8821 0.03547 0.02641 0.0051 0.2799 1.0000
8.000 0.8920 0.03575 0.02676 0.0083 0.2462 1.0000
8.250 0.8986 0.03641 0.02705 0.0123 0.1950 1.0000
8.500 0.8995 0.03822 0.02892 0.0166 0.1566 1.0000
8.750 0.9086 0.03977 0.03037 0.0197 0.1347 1.0000
9.000 0.9173 0.04168 0.03242 0.0225 0.1210 1.0000
9.250 0.9285 0.04305 0.03376 0.0249 0.1099 1.0000
9.500 0.9299 0.04643 0.03770 0.0280 0.1042 1.0000
9.750 0.9403 0.04881 0.04017 0.0301 0.0993 1.0000
10.000 0.9407 0.05235 0.04398 0.0326 0.0967 1.0000
10.250 0.9287 0.05651 0.04858 0.0356 0.0956 1.0000
10.500 0.9121 0.06075 0.05316 0.0383 0.0952 1.0000
10.750 0.8908 0.06502 0.05766 0.0406 0.0954 1.0000
11.000 0.8666 0.06938 0.06216 0.0423 0.0960 1.0000
11.250 0.8428 0.07443 0.06731 0.0422 0.0968 1.0000
11.500 0.8211 0.08017 0.07311 0.0406 0.0975 1.0000
11.750 0.7023 0.10792 0.10068 0.0190 0.1207 1.0000
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Polar data table (+)
Polar graphs
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