GIII BL387 AIRFOIL (giiil-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL387 AIRFOIL (giiil-il) Reynolds number: 50,000 Max Cl/Cd: 31.8 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiil-il-50000-n5.txt Download as CSV file: xf-giiil-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL387 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5429 0.10360 0.09641 -0.0003 1.0000 0.1326
-8.500 -0.5475 0.10030 0.09317 -0.0034 1.0000 0.1393
-8.250 -0.5713 0.09650 0.08950 -0.0118 1.0000 0.1426
-8.000 -0.5412 0.09279 0.08579 -0.0054 1.0000 0.1507
-7.500 -0.5412 0.08543 0.07853 -0.0092 1.0000 0.1673
-6.500 -0.5155 0.06368 0.05606 -0.0242 1.0000 0.0863
-6.000 -0.4903 0.05496 0.04634 -0.0250 1.0000 0.0655
-5.750 -0.4760 0.05157 0.04287 -0.0244 1.0000 0.0643
-5.500 -0.4611 0.04846 0.03956 -0.0237 1.0000 0.0631
-5.250 -0.4454 0.04564 0.03644 -0.0227 1.0000 0.0629
-5.000 -0.4286 0.04307 0.03354 -0.0216 1.0000 0.0635
-4.750 -0.4110 0.04068 0.03080 -0.0204 1.0000 0.0641
-4.500 -0.3925 0.03837 0.02816 -0.0191 1.0000 0.0641
-4.250 -0.3730 0.03617 0.02565 -0.0179 1.0000 0.0638
-4.000 -0.3525 0.03416 0.02334 -0.0166 1.0000 0.0638
-3.750 -0.3312 0.03238 0.02125 -0.0154 1.0000 0.0644
-3.500 -0.3091 0.03107 0.01950 -0.0140 1.0000 0.0663
-3.250 -0.2877 0.02918 0.01757 -0.0132 1.0000 0.0683
-3.000 -0.2651 0.02776 0.01604 -0.0122 1.0000 0.0696
-2.750 -0.2420 0.02651 0.01467 -0.0112 1.0000 0.0709
-2.500 -0.2188 0.02545 0.01353 -0.0101 1.0000 0.0737
-2.250 -0.1953 0.02460 0.01255 -0.0091 1.0000 0.0777
-2.000 -0.1715 0.02386 0.01166 -0.0079 1.0000 0.0801
-1.750 -0.1480 0.02292 0.01077 -0.0071 1.0000 0.0829
-1.500 -0.1271 0.02230 0.01013 -0.0061 1.0000 0.0880
-1.250 -0.1063 0.02185 0.00958 -0.0050 1.0000 0.0942
-1.000 -0.0856 0.02131 0.00906 -0.0042 1.0000 0.0996
-0.750 -0.0559 0.02090 0.00858 -0.0050 0.9956 0.1096
-0.500 -0.0143 0.02023 0.00810 -0.0084 0.9845 0.1386
-0.250 0.0400 0.01726 0.00815 -0.0112 0.9843 1.0000
0.000 0.0836 0.01745 0.00801 -0.0147 0.9699 1.0000
0.250 0.1270 0.01763 0.00798 -0.0182 0.9555 1.0000
0.500 0.1706 0.01780 0.00799 -0.0216 0.9408 1.0000
0.750 0.2130 0.01794 0.00804 -0.0247 0.9255 1.0000
1.000 0.2528 0.01806 0.00810 -0.0271 0.9089 1.0000
1.250 0.2906 0.01815 0.00817 -0.0289 0.8910 1.0000
1.500 0.3273 0.01821 0.00821 -0.0303 0.8719 1.0000
1.750 0.3587 0.01827 0.00826 -0.0305 0.8495 1.0000
2.000 0.3889 0.01830 0.00828 -0.0302 0.8263 1.0000
2.250 0.4164 0.01834 0.00832 -0.0294 0.8018 1.0000
2.500 0.4429 0.01837 0.00835 -0.0283 0.7766 1.0000
2.750 0.4669 0.01845 0.00841 -0.0268 0.7491 1.0000
3.000 0.4907 0.01853 0.00847 -0.0251 0.7210 1.0000
3.250 0.5139 0.01863 0.00853 -0.0234 0.6910 1.0000
3.500 0.5363 0.01874 0.00863 -0.0215 0.6576 1.0000
3.750 0.5584 0.01887 0.00867 -0.0196 0.6211 1.0000
4.000 0.5800 0.01906 0.00875 -0.0176 0.5809 1.0000
4.250 0.6010 0.01933 0.00888 -0.0156 0.5377 1.0000
4.500 0.6218 0.01972 0.00910 -0.0138 0.4911 1.0000
4.750 0.6421 0.02022 0.00944 -0.0121 0.4393 1.0000
5.000 0.6617 0.02081 0.00985 -0.0105 0.3803 1.0000
5.250 0.6803 0.02160 0.01034 -0.0090 0.3167 1.0000
5.500 0.6987 0.02264 0.01102 -0.0076 0.2640 1.0000
5.750 0.7179 0.02379 0.01191 -0.0066 0.2240 1.0000
6.000 0.7378 0.02496 0.01291 -0.0056 0.1947 1.0000
6.250 0.7581 0.02612 0.01399 -0.0047 0.1727 1.0000
6.500 0.7788 0.02730 0.01509 -0.0038 0.1561 1.0000
6.750 0.8000 0.02847 0.01625 -0.0029 0.1422 1.0000
7.000 0.8221 0.02970 0.01756 -0.0021 0.1311 1.0000
7.250 0.8438 0.03099 0.01890 -0.0013 0.1215 1.0000
7.500 0.8660 0.03235 0.02031 -0.0005 0.1140 1.0000
7.750 0.8885 0.03392 0.02203 0.0002 0.1074 1.0000
8.000 0.9096 0.03538 0.02361 0.0009 0.1009 1.0000
8.250 0.9312 0.03720 0.02555 0.0015 0.0963 1.0000
8.500 0.9512 0.03931 0.02804 0.0024 0.0919 1.0000
8.750 0.9699 0.04114 0.03003 0.0031 0.0875 1.0000
9.000 0.9877 0.04326 0.03224 0.0039 0.0839 1.0000
9.250 1.0004 0.04621 0.03577 0.0050 0.0812 1.0000
9.500 1.0108 0.04919 0.03916 0.0061 0.0785 1.0000
9.750 1.0209 0.05176 0.04200 0.0072 0.0757 1.0000
10.000 1.0336 0.05398 0.04427 0.0079 0.0731 1.0000
10.250 1.0348 0.05756 0.04819 0.0091 0.0716 1.0000
10.500 1.0255 0.06189 0.05300 0.0103 0.0708 1.0000
10.750 1.0098 0.06644 0.05791 0.0112 0.0703 1.0000
11.000 0.9873 0.07112 0.06285 0.0117 0.0702 1.0000
11.250 0.9610 0.07684 0.06877 0.0101 0.0703 1.0000
11.500 0.9316 0.08413 0.07621 0.0060 0.0707 1.0000
11.750 0.9015 0.09328 0.08544 -0.0003 0.0712 1.0000
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Polar data table (+)
Polar graphs
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