GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL145 AIRFOIL (giiif-il) Reynolds number: 200,000 Max Cl/Cd: 55.89 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiif-il-200000-n5.txt Download as CSV file: xf-giiif-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL145 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5792 0.08683 0.08345 -0.0093 1.0000 0.0111
-8.500 -0.5830 0.08137 0.07804 -0.0142 1.0000 0.0109
-8.250 -0.5890 0.07595 0.07261 -0.0190 1.0000 0.0107
-8.000 -0.5908 0.07057 0.06718 -0.0224 1.0000 0.0106
-7.750 -0.5903 0.06521 0.06173 -0.0249 1.0000 0.0105
-7.500 -0.5874 0.05986 0.05624 -0.0264 1.0000 0.0104
-7.250 -0.5816 0.05486 0.05108 -0.0272 1.0000 0.0106
-7.000 -0.5729 0.05015 0.04616 -0.0273 1.0000 0.0113
-6.750 -0.5632 0.04516 0.04091 -0.0266 1.0000 0.0121
-6.500 -0.5533 0.03999 0.03541 -0.0253 1.0000 0.0125
-6.250 -0.5443 0.03478 0.02979 -0.0231 1.0000 0.0125
-6.000 -0.5344 0.03005 0.02457 -0.0205 1.0000 0.0126
-5.750 -0.5215 0.02631 0.02029 -0.0180 1.0000 0.0129
-5.500 -0.5058 0.02360 0.01710 -0.0159 1.0000 0.0134
-5.250 -0.4775 0.02073 0.01370 -0.0162 0.9958 0.0141
-5.000 -0.4459 0.01908 0.01185 -0.0176 0.9900 0.0167
-4.750 -0.4124 0.01780 0.01030 -0.0189 0.9848 0.0190
-4.500 -0.3803 0.01638 0.00865 -0.0198 0.9784 0.0209
-4.250 -0.3483 0.01550 0.00760 -0.0207 0.9712 0.0229
-4.000 -0.3170 0.01441 0.00648 -0.0218 0.9645 0.0275
-3.750 -0.2866 0.01368 0.00566 -0.0224 0.9557 0.0318
-3.500 -0.2563 0.01301 0.00491 -0.0231 0.9472 0.0389
-3.250 -0.2250 0.01258 0.00450 -0.0240 0.9394 0.0534
-3.000 -0.1958 0.01222 0.00412 -0.0244 0.9299 0.0697
-2.750 -0.1667 0.01189 0.00379 -0.0248 0.9210 0.0881
-2.500 -0.1383 0.01153 0.00348 -0.0251 0.9123 0.1102
-2.250 -0.1117 0.01118 0.00318 -0.0250 0.9026 0.1424
-2.000 -0.0870 0.01055 0.00291 -0.0247 0.8936 0.2417
-1.500 -0.0534 0.00863 0.00283 -0.0200 0.8748 0.7637
-1.250 -0.0289 0.00857 0.00281 -0.0188 0.8670 0.8099
-1.000 -0.0038 0.00855 0.00280 -0.0177 0.8591 0.8422
-0.750 0.0217 0.00856 0.00281 -0.0167 0.8512 0.8688
-0.500 0.0486 0.00860 0.00284 -0.0160 0.8440 0.8928
-0.250 0.0775 0.00867 0.00290 -0.0157 0.8369 0.9179
0.000 0.1084 0.00873 0.00291 -0.0160 0.8300 0.9343
0.250 0.1392 0.00875 0.00287 -0.0166 0.8204 0.9415
0.500 0.1700 0.00876 0.00282 -0.0171 0.8093 0.9483
0.750 0.2011 0.00877 0.00278 -0.0178 0.7975 0.9548
1.000 0.2330 0.00880 0.00274 -0.0187 0.7863 0.9612
1.250 0.2652 0.00882 0.00275 -0.0196 0.7745 0.9676
1.500 0.2980 0.00884 0.00278 -0.0208 0.7638 0.9741
1.750 0.3318 0.00887 0.00281 -0.0222 0.7535 0.9796
2.000 0.3652 0.00890 0.00285 -0.0235 0.7428 0.9857
2.500 0.4342 0.00896 0.00300 -0.0266 0.7179 0.9963
2.750 0.4654 0.00900 0.00308 -0.0275 0.7035 1.0000
3.000 0.4881 0.00905 0.00309 -0.0264 0.6739 1.0000
3.250 0.5090 0.00920 0.00304 -0.0248 0.6162 1.0000
3.500 0.5298 0.00948 0.00311 -0.0234 0.5455 1.0000
3.750 0.5482 0.01005 0.00324 -0.0217 0.4397 1.0000
4.000 0.5655 0.01089 0.00358 -0.0201 0.3374 1.0000
4.250 0.5833 0.01175 0.00400 -0.0188 0.2354 1.0000
4.500 0.5995 0.01293 0.00455 -0.0173 0.1133 1.0000
4.750 0.6191 0.01375 0.00515 -0.0162 0.0650 1.0000
5.000 0.6407 0.01436 0.00574 -0.0153 0.0481 1.0000
5.250 0.6622 0.01502 0.00643 -0.0143 0.0390 1.0000
5.500 0.6836 0.01571 0.00714 -0.0133 0.0317 1.0000
5.750 0.7047 0.01647 0.00801 -0.0123 0.0286 1.0000
6.000 0.7258 0.01729 0.00895 -0.0112 0.0259 1.0000
6.250 0.7473 0.01807 0.00979 -0.0103 0.0228 1.0000
6.500 0.7654 0.01952 0.01132 -0.0090 0.0197 1.0000
6.750 0.7869 0.02059 0.01253 -0.0080 0.0185 1.0000
7.000 0.8084 0.02189 0.01400 -0.0069 0.0170 1.0000
7.250 0.8305 0.02283 0.01508 -0.0062 0.0147 1.0000
7.500 0.8516 0.02389 0.01625 -0.0054 0.0132 1.0000
7.750 0.8704 0.02603 0.01859 -0.0043 0.0122 1.0000
8.000 0.8871 0.02920 0.02214 -0.0029 0.0115 1.0000
8.250 0.9042 0.03169 0.02504 -0.0014 0.0111 1.0000
8.500 0.9181 0.03462 0.02842 0.0002 0.0106 1.0000
8.750 0.9300 0.03745 0.03174 0.0019 0.0098 1.0000
9.000 0.9401 0.04011 0.03475 0.0034 0.0089 1.0000
9.250 0.9463 0.04303 0.03799 0.0051 0.0084 1.0000
9.500 0.9454 0.04685 0.04218 0.0070 0.0082 1.0000
9.750 0.9391 0.05087 0.04653 0.0090 0.0080 1.0000
10.000 0.9252 0.05495 0.05087 0.0111 0.0080 1.0000
10.250 0.9061 0.05954 0.05570 0.0121 0.0080 1.0000
10.500 0.8834 0.06529 0.06167 0.0108 0.0081 1.0000
10.750 0.8585 0.07268 0.06923 0.0068 0.0083 1.0000
11.000 0.8323 0.08292 0.07962 -0.0007 0.0086 1.0000
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