GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL167 AIRFOIL (giiig-il) Reynolds number: 200,000 Max Cl/Cd: 56.11 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiig-il-200000-n5.txt Download as CSV file: xf-giiig-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL167 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4637 0.08471 0.08143 -0.0138 1.0000 0.0157
-9.000 -0.4695 0.07960 0.07635 -0.0156 1.0000 0.0153
-8.750 -0.4769 0.07430 0.07108 -0.0178 1.0000 0.0149
-8.500 -0.4868 0.06861 0.06543 -0.0208 1.0000 0.0146
-8.250 -0.5020 0.06245 0.05930 -0.0257 1.0000 0.0142
-8.000 -0.5968 0.06594 0.06244 -0.0254 1.0000 0.0122
-7.750 -0.5966 0.06080 0.05718 -0.0268 1.0000 0.0124
-7.500 -0.5928 0.05572 0.05194 -0.0275 1.0000 0.0125
-7.250 -0.5860 0.05022 0.04620 -0.0275 1.0000 0.0123
-7.000 -0.5782 0.04493 0.04064 -0.0268 1.0000 0.0122
-6.750 -0.5709 0.03949 0.03485 -0.0254 1.0000 0.0122
-6.500 -0.5639 0.03424 0.02915 -0.0234 1.0000 0.0123
-6.250 -0.5539 0.03022 0.02469 -0.0213 1.0000 0.0127
-6.000 -0.5400 0.02754 0.02166 -0.0194 1.0000 0.0132
-5.750 -0.5242 0.02537 0.01918 -0.0176 1.0000 0.0139
-5.500 -0.5067 0.02418 0.01778 -0.0160 1.0000 0.0153
-5.250 -0.4772 0.02206 0.01524 -0.0166 0.9957 0.0173
-5.000 -0.4451 0.01973 0.01245 -0.0175 0.9904 0.0185
-4.750 -0.4114 0.01814 0.01055 -0.0187 0.9858 0.0194
-4.500 -0.3804 0.01674 0.00901 -0.0198 0.9793 0.0226
-4.250 -0.3482 0.01578 0.00793 -0.0209 0.9728 0.0251
-4.000 -0.3163 0.01479 0.00682 -0.0218 0.9660 0.0276
-3.750 -0.2862 0.01395 0.00588 -0.0224 0.9576 0.0306
-3.500 -0.2543 0.01340 0.00532 -0.0235 0.9506 0.0379
-3.250 -0.2247 0.01283 0.00470 -0.0240 0.9416 0.0459
-3.000 -0.1948 0.01243 0.00424 -0.0246 0.9330 0.0566
-2.750 -0.1649 0.01204 0.00386 -0.0251 0.9250 0.0713
-2.500 -0.1374 0.01168 0.00355 -0.0252 0.9154 0.0912
-2.250 -0.1100 0.01130 0.00323 -0.0252 0.9065 0.1224
-2.000 -0.0844 0.01073 0.00295 -0.0251 0.8978 0.2079
-1.750 -0.0745 0.00883 0.00282 -0.0220 0.8872 0.6670
-1.500 -0.0517 0.00864 0.00286 -0.0204 0.8789 0.7613
-1.250 -0.0271 0.00857 0.00284 -0.0191 0.8708 0.8081
-1.000 -0.0024 0.00855 0.00286 -0.0179 0.8626 0.8440
-0.750 0.0233 0.00857 0.00288 -0.0168 0.8556 0.8745
-0.500 0.0493 0.00865 0.00298 -0.0156 0.8474 0.9099
0.000 0.1100 0.00873 0.00295 -0.0162 0.8324 0.9364
0.250 0.1416 0.00874 0.00289 -0.0169 0.8223 0.9423
0.500 0.1716 0.00875 0.00283 -0.0173 0.8102 0.9498
0.750 0.2036 0.00876 0.00278 -0.0181 0.7977 0.9556
1.000 0.2349 0.00878 0.00276 -0.0189 0.7862 0.9628
1.250 0.2682 0.00880 0.00276 -0.0201 0.7754 0.9685
1.500 0.3003 0.00883 0.00279 -0.0211 0.7650 0.9755
1.750 0.3349 0.00885 0.00281 -0.0226 0.7544 0.9805
2.000 0.3683 0.00889 0.00285 -0.0239 0.7432 0.9865
2.250 0.4031 0.00891 0.00292 -0.0256 0.7306 0.9917
2.500 0.4374 0.00894 0.00299 -0.0271 0.7169 0.9973
2.750 0.4664 0.00898 0.00305 -0.0275 0.7001 1.0000
3.000 0.4886 0.00905 0.00303 -0.0262 0.6631 1.0000
3.250 0.5101 0.00921 0.00304 -0.0248 0.6104 1.0000
3.500 0.5314 0.00947 0.00310 -0.0235 0.5482 1.0000
3.750 0.5492 0.01009 0.00322 -0.0217 0.4359 1.0000
4.000 0.5670 0.01087 0.00355 -0.0202 0.3410 1.0000
4.250 0.5847 0.01175 0.00395 -0.0188 0.2378 1.0000
4.500 0.6022 0.01274 0.00444 -0.0175 0.1334 1.0000
4.750 0.6213 0.01362 0.00504 -0.0163 0.0756 1.0000
5.000 0.6425 0.01428 0.00559 -0.0154 0.0524 1.0000
5.250 0.6646 0.01485 0.00619 -0.0145 0.0424 1.0000
5.500 0.6860 0.01555 0.00695 -0.0135 0.0367 1.0000
5.750 0.7079 0.01619 0.00769 -0.0125 0.0327 1.0000
6.000 0.7286 0.01701 0.00857 -0.0116 0.0283 1.0000
6.250 0.7489 0.01796 0.00961 -0.0104 0.0262 1.0000
6.500 0.7701 0.01887 0.01065 -0.0094 0.0243 1.0000
6.750 0.7920 0.01964 0.01152 -0.0086 0.0214 1.0000
7.000 0.8131 0.02058 0.01252 -0.0077 0.0192 1.0000
7.250 0.8307 0.02281 0.01486 -0.0063 0.0174 1.0000
7.500 0.8529 0.02403 0.01629 -0.0054 0.0164 1.0000
7.750 0.8747 0.02513 0.01766 -0.0046 0.0145 1.0000
8.000 0.8953 0.02654 0.01928 -0.0037 0.0131 1.0000
8.250 0.9145 0.02823 0.02120 -0.0027 0.0122 1.0000
8.500 0.9320 0.03008 0.02327 -0.0017 0.0115 1.0000
8.750 0.9456 0.03277 0.02627 -0.0003 0.0109 1.0000
9.000 0.9503 0.03731 0.03133 0.0019 0.0105 1.0000
9.250 0.9579 0.04031 0.03476 0.0037 0.0102 1.0000
9.500 0.9616 0.04364 0.03854 0.0057 0.0097 1.0000
9.750 0.9587 0.04758 0.04290 0.0078 0.0092 1.0000
10.000 0.9490 0.05167 0.04734 0.0100 0.0089 1.0000
10.250 0.9332 0.05572 0.05165 0.0119 0.0087 1.0000
10.500 0.9142 0.06037 0.05651 0.0121 0.0087 1.0000
10.750 0.8936 0.06590 0.06224 0.0102 0.0088 1.0000
11.000 0.8721 0.07269 0.06920 0.0061 0.0090 1.0000
11.250 0.8508 0.08128 0.07790 -0.0005 0.0094 1.0000
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Polar data table (+)
Polar graphs
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