GIII BL207 AIRFOIL (giiih-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GIII BL207 AIRFOIL (giiih-il) Reynolds number: 200,000 Max Cl/Cd: 55.34 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiih-il-200000-n5.txt Download as CSV file: xf-giiih-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL207 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4535 0.10207 0.09867 -0.0085 1.0000 0.0173
-10.000 -0.4615 0.09610 0.09275 -0.0106 1.0000 0.0159
-9.500 -0.5824 0.09690 0.09341 -0.0048 1.0000 0.0143
-9.250 -0.5835 0.09225 0.08879 -0.0072 1.0000 0.0141
-9.000 -0.5853 0.08732 0.08389 -0.0104 1.0000 0.0139
-8.750 -0.5885 0.08195 0.07856 -0.0150 1.0000 0.0138
-8.500 -0.5943 0.07656 0.07317 -0.0199 1.0000 0.0136
-8.250 -0.5975 0.07146 0.06802 -0.0229 1.0000 0.0135
-8.000 -0.5982 0.06623 0.06270 -0.0253 1.0000 0.0134
-7.750 -0.5967 0.06097 0.05731 -0.0269 1.0000 0.0134
-7.500 -0.5930 0.05572 0.05188 -0.0277 1.0000 0.0134
-7.250 -0.5874 0.05038 0.04631 -0.0277 1.0000 0.0135
-7.000 -0.5803 0.04474 0.04035 -0.0269 1.0000 0.0139
-6.750 -0.5735 0.03849 0.03365 -0.0252 1.0000 0.0148
-6.500 -0.5615 0.03628 0.03125 -0.0240 1.0000 0.0156
-6.250 -0.5491 0.03328 0.02796 -0.0222 1.0000 0.0161
-6.000 -0.5362 0.03026 0.02460 -0.0202 1.0000 0.0165
-5.750 -0.5220 0.02753 0.02149 -0.0180 1.0000 0.0171
-5.500 -0.5068 0.02508 0.01866 -0.0159 1.0000 0.0178
-5.250 -0.4769 0.02291 0.01608 -0.0166 0.9957 0.0198
-5.000 -0.4446 0.02089 0.01361 -0.0175 0.9906 0.0212
-4.750 -0.4111 0.01918 0.01157 -0.0187 0.9862 0.0220
-4.500 -0.3803 0.01724 0.00945 -0.0196 0.9806 0.0236
-4.250 -0.3469 0.01642 0.00853 -0.0210 0.9756 0.0257
-4.000 -0.3156 0.01576 0.00778 -0.0219 0.9683 0.0289
-3.750 -0.2836 0.01487 0.00678 -0.0228 0.9622 0.0312
-3.500 -0.2540 0.01390 0.00578 -0.0234 0.9544 0.0343
-3.250 -0.2234 0.01335 0.00519 -0.0241 0.9467 0.0390
-3.000 -0.1925 0.01296 0.00473 -0.0249 0.9393 0.0457
-2.750 -0.1637 0.01249 0.00426 -0.0253 0.9307 0.0540
-2.500 -0.1339 0.01208 0.00382 -0.0258 0.9233 0.0629
-2.250 -0.1064 0.01177 0.00345 -0.0257 0.9139 0.0726
-2.000 -0.0792 0.01137 0.00315 -0.0257 0.9055 0.0996
-1.750 -0.0556 0.01050 0.00287 -0.0254 0.8967 0.2533
-1.500 -0.0455 0.00878 0.00283 -0.0220 0.8864 0.6963
-1.250 -0.0220 0.00863 0.00285 -0.0205 0.8786 0.7770
-1.000 0.0015 0.00856 0.00291 -0.0188 0.8702 0.8332
-0.750 0.0253 0.00858 0.00300 -0.0171 0.8623 0.8804
-0.500 0.0530 0.00864 0.00304 -0.0163 0.8548 0.9073
-0.250 0.0836 0.00870 0.00306 -0.0164 0.8463 0.9272
0.000 0.1133 0.00871 0.00299 -0.0166 0.8350 0.9378
0.250 0.1448 0.00871 0.00291 -0.0172 0.8219 0.9439
0.500 0.1748 0.00872 0.00284 -0.0175 0.8105 0.9517
0.750 0.2081 0.00873 0.00282 -0.0187 0.7999 0.9576
1.000 0.2394 0.00875 0.00281 -0.0195 0.7891 0.9650
1.250 0.2732 0.00877 0.00280 -0.0208 0.7781 0.9707
1.500 0.3057 0.00880 0.00280 -0.0218 0.7668 0.9772
1.750 0.3400 0.00882 0.00282 -0.0233 0.7547 0.9828
2.000 0.3742 0.00884 0.00285 -0.0247 0.7417 0.9884
2.250 0.4082 0.00887 0.00290 -0.0262 0.7277 0.9942
2.500 0.4427 0.00890 0.00294 -0.0277 0.7120 0.9995
2.750 0.4669 0.00895 0.00297 -0.0270 0.6871 1.0000
3.000 0.4887 0.00907 0.00292 -0.0256 0.6414 1.0000
3.250 0.5103 0.00928 0.00297 -0.0243 0.5876 1.0000
3.500 0.5313 0.00960 0.00304 -0.0230 0.5171 1.0000
3.750 0.5500 0.01019 0.00320 -0.0214 0.4261 1.0000
4.000 0.5693 0.01083 0.00350 -0.0201 0.3500 1.0000
4.250 0.5882 0.01157 0.00388 -0.0188 0.2643 1.0000
4.500 0.6068 0.01242 0.00431 -0.0176 0.1734 1.0000
4.750 0.6257 0.01331 0.00483 -0.0165 0.1022 1.0000
5.000 0.6467 0.01400 0.00535 -0.0155 0.0707 1.0000
5.250 0.6686 0.01459 0.00591 -0.0147 0.0563 1.0000
5.500 0.6911 0.01514 0.00649 -0.0139 0.0470 1.0000
5.750 0.7130 0.01578 0.00718 -0.0130 0.0399 1.0000
6.000 0.7352 0.01639 0.00788 -0.0122 0.0355 1.0000
6.250 0.7558 0.01727 0.00879 -0.0111 0.0319 1.0000
6.500 0.7764 0.01819 0.00980 -0.0101 0.0298 1.0000
6.750 0.7985 0.01891 0.01063 -0.0093 0.0269 1.0000
7.000 0.8201 0.01974 0.01158 -0.0084 0.0246 1.0000
7.250 0.8408 0.02078 0.01269 -0.0075 0.0228 1.0000
7.500 0.8596 0.02242 0.01441 -0.0064 0.0209 1.0000
7.750 0.8820 0.02326 0.01544 -0.0056 0.0191 1.0000
8.000 0.9029 0.02465 0.01703 -0.0047 0.0177 1.0000
8.250 0.9232 0.02616 0.01874 -0.0037 0.0165 1.0000
8.500 0.9428 0.02748 0.02021 -0.0029 0.0153 1.0000
8.750 0.9595 0.02926 0.02218 -0.0019 0.0140 1.0000
9.000 0.9759 0.03129 0.02457 -0.0007 0.0130 1.0000
9.250 0.9896 0.03388 0.02756 0.0008 0.0123 1.0000
9.500 0.9991 0.03698 0.03110 0.0026 0.0117 1.0000
9.750 1.0036 0.04044 0.03500 0.0046 0.0113 1.0000
10.000 1.0027 0.04419 0.03917 0.0068 0.0110 1.0000
10.250 0.9957 0.04817 0.04351 0.0090 0.0108 1.0000
10.500 0.9810 0.05206 0.04771 0.0114 0.0107 1.0000
10.750 0.9621 0.05644 0.05236 0.0126 0.0107 1.0000
11.000 0.9402 0.06172 0.05787 0.0118 0.0107 1.0000
11.250 0.9159 0.06832 0.06469 0.0087 0.0108 1.0000
11.500 0.8890 0.07715 0.07370 0.0025 0.0110 1.0000
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Polar data table (+)
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