GIII BL45 AIRFOIL (giiib-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL45 AIRFOIL (giiib-il) Reynolds number: 50,000 Max Cl/Cd: 28.58 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiib-il-50000.txt Download as CSV file: xf-giiib-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL45 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5573 0.09199 0.08549 0.0182 1.0000 0.4080
-7.750 -0.6851 0.06943 0.06246 -0.0174 1.0000 0.1620
-7.500 -0.6733 0.06281 0.05571 -0.0175 1.0000 0.1448
-7.250 -0.6778 0.05734 0.04967 -0.0163 1.0000 0.1322
-7.000 -0.6686 0.05309 0.04521 -0.0149 1.0000 0.1297
-6.750 -0.6613 0.04884 0.04056 -0.0129 1.0000 0.1255
-6.500 -0.6578 0.04503 0.03575 -0.0095 1.0000 0.1198
-6.250 -0.6435 0.04164 0.03187 -0.0073 1.0000 0.1195
-6.000 -0.6255 0.03855 0.02880 -0.0059 1.0000 0.1239
-5.750 -0.6090 0.03617 0.02604 -0.0038 1.0000 0.1301
-5.500 -0.5901 0.03355 0.02289 -0.0017 1.0000 0.1345
-5.250 -0.5678 0.03127 0.02053 -0.0005 1.0000 0.1439
-5.000 -0.5459 0.02930 0.01840 0.0010 1.0000 0.1588
-4.750 -0.5199 0.02722 0.01624 0.0019 1.0000 0.1788
-4.500 -0.4919 0.02520 0.01439 0.0026 1.0000 0.2139
-4.250 -0.4650 0.02294 0.01258 0.0033 1.0000 0.2830
-4.000 -0.4545 0.01997 0.01099 0.0066 1.0000 0.4252
-3.750 -0.1336 0.02310 0.01354 -0.0279 1.0000 1.0000
-3.500 -0.1160 0.02248 0.01273 -0.0277 1.0000 1.0000
-3.250 -0.0984 0.02193 0.01203 -0.0274 1.0000 1.0000
-3.000 -0.0810 0.02146 0.01141 -0.0270 1.0000 1.0000
-2.750 -0.0641 0.02104 0.01085 -0.0263 1.0000 1.0000
-2.500 -0.0478 0.02069 0.01040 -0.0255 1.0000 1.0000
-2.250 -0.0328 0.02039 0.01002 -0.0245 1.0000 1.0000
-2.000 -0.0197 0.02015 0.00973 -0.0231 1.0000 1.0000
-1.750 -0.0094 0.01999 0.00952 -0.0211 1.0000 1.0000
-1.500 -0.0029 0.01991 0.00941 -0.0185 1.0000 1.0000
-1.250 0.0001 0.01990 0.00938 -0.0154 1.0000 1.0000
-1.000 0.0003 0.01996 0.00941 -0.0117 1.0000 1.0000
-0.750 -0.0012 0.02006 0.00948 -0.0078 1.0000 1.0000
-0.500 -0.0032 0.02019 0.00958 -0.0039 1.0000 1.0000
-0.250 -0.0050 0.02036 0.00972 -0.0001 1.0000 1.0000
0.000 -0.0061 0.02056 0.00988 0.0036 1.0000 1.0000
0.250 -0.0058 0.02081 0.01007 0.0070 1.0000 1.0000
0.500 -0.0039 0.02109 0.01031 0.0100 1.0000 1.0000
0.750 -0.0003 0.02142 0.01059 0.0127 1.0000 1.0000
1.000 0.0050 0.02180 0.01093 0.0150 1.0000 1.0000
1.250 0.0119 0.02223 0.01132 0.0170 1.0000 1.0000
1.500 0.0206 0.02272 0.01178 0.0186 1.0000 1.0000
1.750 0.0307 0.02326 0.01230 0.0199 1.0000 1.0000
2.000 0.0859 0.02438 0.01348 0.0126 0.9847 1.0000
2.250 0.1720 0.02554 0.01481 0.0002 0.9560 1.0000
2.500 0.2598 0.02615 0.01566 -0.0114 0.9246 1.0000
2.750 0.3448 0.02631 0.01614 -0.0216 0.8962 1.0000
3.000 0.4237 0.02601 0.01617 -0.0298 0.8678 1.0000
3.250 0.4801 0.02557 0.01604 -0.0332 0.8386 1.0000
3.500 0.5171 0.02521 0.01590 -0.0329 0.8068 1.0000
3.750 0.5482 0.02474 0.01562 -0.0311 0.7727 1.0000
4.000 0.5780 0.02398 0.01503 -0.0283 0.7362 1.0000
4.250 0.6017 0.02330 0.01441 -0.0244 0.6938 1.0000
4.500 0.6216 0.02293 0.01402 -0.0202 0.6429 1.0000
4.750 0.6425 0.02288 0.01380 -0.0166 0.5912 1.0000
5.000 0.6622 0.02333 0.01414 -0.0138 0.5438 1.0000
5.250 0.6837 0.02392 0.01457 -0.0116 0.5071 1.0000
5.500 0.7045 0.02475 0.01538 -0.0099 0.4766 1.0000
5.750 0.7255 0.02561 0.01627 -0.0083 0.4508 1.0000
6.000 0.7457 0.02661 0.01739 -0.0068 0.4278 1.0000
6.250 0.7675 0.02747 0.01826 -0.0052 0.4056 1.0000
6.500 0.7861 0.02814 0.01890 -0.0031 0.3775 1.0000
6.750 0.7996 0.02860 0.01938 -0.0003 0.3414 1.0000
7.000 0.8132 0.02918 0.01979 0.0025 0.3021 1.0000
7.250 0.8233 0.03032 0.02071 0.0057 0.2524 1.0000
7.500 0.8294 0.03222 0.02225 0.0095 0.1931 1.0000
7.750 0.8389 0.03423 0.02422 0.0125 0.1554 1.0000
8.000 0.8548 0.03632 0.02620 0.0146 0.1341 1.0000
8.250 0.8697 0.03849 0.02854 0.0167 0.1197 1.0000
8.500 0.8873 0.04070 0.03070 0.0181 0.1092 1.0000
8.750 0.8970 0.04430 0.03499 0.0206 0.1050 1.0000
9.000 0.9059 0.04765 0.03874 0.0227 0.1010 1.0000
9.250 0.9201 0.05051 0.04154 0.0240 0.0960 1.0000
9.500 0.9160 0.05450 0.04611 0.0266 0.0946 1.0000
9.750 0.9086 0.05873 0.05079 0.0289 0.0939 1.0000
10.000 0.8974 0.06313 0.05553 0.0308 0.0938 1.0000
10.250 0.8830 0.06764 0.06028 0.0323 0.0943 1.0000
10.500 0.8655 0.07209 0.06490 0.0335 0.0950 1.0000
10.750 0.8479 0.07670 0.06960 0.0339 0.0957 1.0000
11.000 0.8346 0.08177 0.07472 0.0333 0.0963 1.0000
11.250 0.7567 0.09627 0.08932 0.0218 0.1084 1.0000
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Polar data table (+)
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