GIII BL387 AIRFOIL (giiil-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL387 AIRFOIL (giiil-il) Reynolds number: 50,000 Max Cl/Cd: 31.52 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiil-il-50000.txt Download as CSV file: xf-giiil-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5421 0.11123 0.10407 0.0111 1.0000 0.2262
-8.750 -0.5407 0.10787 0.10078 0.0106 1.0000 0.2378
-8.500 -0.5618 0.10647 0.09951 0.0073 1.0000 0.2482
-8.250 -0.5334 0.10139 0.09441 0.0109 1.0000 0.2691
-7.750 -0.5329 0.09590 0.08906 0.0118 1.0000 0.3100
-7.500 -0.5137 0.09213 0.08530 0.0146 1.0000 0.3369
-7.250 -0.5047 0.08909 0.08230 0.0166 1.0000 0.3659
-7.000 -0.4964 0.08647 0.07973 0.0193 1.0000 0.4017
-6.750 -0.4773 0.08342 0.07670 0.0229 1.0000 0.4457
-6.500 -0.4665 0.08128 0.07460 0.0270 1.0000 0.4979
-6.250 -0.4278 0.07790 0.07118 0.0319 1.0000 0.5747
-6.000 -0.3829 0.07395 0.06719 0.0351 1.0000 0.6610
-5.750 -0.3387 0.06965 0.06286 0.0356 1.0000 0.7403
-5.500 -0.2972 0.06507 0.05824 0.0336 1.0000 0.8051
-5.250 -0.2727 0.06163 0.05481 0.0324 1.0000 0.8477
-4.500 -0.4167 0.05647 0.05035 0.0322 1.0000 0.5978
-4.250 -0.4175 0.04118 0.03307 -0.0165 1.0000 0.2455
-4.000 -0.3860 0.03792 0.02898 -0.0173 1.0000 0.1964
-3.750 -0.3576 0.03599 0.02613 -0.0165 1.0000 0.1688
-3.500 -0.3349 0.03314 0.02318 -0.0156 1.0000 0.1605
-3.250 -0.3095 0.03197 0.02129 -0.0142 1.0000 0.1530
-3.000 -0.2861 0.02998 0.01913 -0.0132 1.0000 0.1520
-2.750 -0.2617 0.02819 0.01717 -0.0122 1.0000 0.1500
-2.500 -0.2368 0.02669 0.01548 -0.0112 1.0000 0.1483
-2.250 -0.2117 0.02548 0.01408 -0.0102 1.0000 0.1498
-2.000 -0.1864 0.02449 0.01292 -0.0092 1.0000 0.1536
-1.750 -0.1595 0.02324 0.01173 -0.0084 1.0000 0.1575
-1.500 -0.1339 0.02239 0.01085 -0.0075 1.0000 0.1633
-1.250 -0.1112 0.02160 0.01009 -0.0064 1.0000 0.1738
-1.000 -0.0894 0.02092 0.00942 -0.0053 1.0000 0.1867
-0.750 -0.0673 0.02015 0.00879 -0.0046 1.0000 0.2079
-0.500 -0.0115 0.01696 0.00842 -0.0064 1.0000 1.0000
-0.250 0.0024 0.01717 0.00819 -0.0043 1.0000 1.0000
0.000 0.0170 0.01741 0.00815 -0.0027 1.0000 1.0000
0.250 0.0325 0.01771 0.00823 -0.0015 1.0000 1.0000
0.500 0.0487 0.01807 0.00843 -0.0006 1.0000 1.0000
0.750 0.0652 0.01851 0.00873 0.0001 1.0000 1.0000
1.000 0.0818 0.01902 0.00914 0.0005 1.0000 1.0000
1.250 0.0983 0.01962 0.00965 0.0007 1.0000 1.0000
1.500 0.1147 0.02032 0.01028 0.0007 1.0000 1.0000
1.750 0.1468 0.02125 0.01117 -0.0023 0.9939 1.0000
2.000 0.2166 0.02243 0.01235 -0.0119 0.9697 1.0000
2.250 0.2823 0.02333 0.01333 -0.0202 0.9435 1.0000
2.500 0.3418 0.02397 0.01408 -0.0266 0.9155 1.0000
2.750 0.4038 0.02431 0.01459 -0.0327 0.8868 1.0000
3.000 0.4623 0.02429 0.01478 -0.0370 0.8574 1.0000
3.250 0.5110 0.02401 0.01467 -0.0386 0.8266 1.0000
3.500 0.5494 0.02357 0.01439 -0.0378 0.7934 1.0000
3.750 0.5808 0.02301 0.01393 -0.0352 0.7579 1.0000
4.000 0.6088 0.02231 0.01327 -0.0316 0.7208 1.0000
4.250 0.6297 0.02192 0.01290 -0.0276 0.6768 1.0000
4.500 0.6507 0.02150 0.01237 -0.0233 0.6276 1.0000
4.750 0.6695 0.02138 0.01203 -0.0191 0.5661 1.0000
5.000 0.6864 0.02178 0.01202 -0.0151 0.4892 1.0000
5.250 0.7024 0.02273 0.01242 -0.0117 0.4069 1.0000
5.500 0.7198 0.02391 0.01316 -0.0093 0.3390 1.0000
5.750 0.7406 0.02539 0.01425 -0.0077 0.2924 1.0000
6.000 0.7635 0.02703 0.01566 -0.0065 0.2596 1.0000
6.250 0.7868 0.02876 0.01733 -0.0056 0.2351 1.0000
6.500 0.8105 0.03062 0.01923 -0.0047 0.2169 1.0000
6.750 0.8333 0.03253 0.02122 -0.0039 0.2016 1.0000
7.000 0.8561 0.03479 0.02363 -0.0031 0.1909 1.0000
7.250 0.8789 0.03698 0.02586 -0.0024 0.1808 1.0000
7.500 0.8958 0.03969 0.02914 -0.0012 0.1730 1.0000
7.750 0.9161 0.04243 0.03205 -0.0004 0.1674 1.0000
8.000 0.9303 0.04583 0.03585 0.0007 0.1629 1.0000
8.250 0.9382 0.04958 0.04019 0.0019 0.1591 1.0000
8.500 0.9441 0.05386 0.04496 0.0028 0.1574 1.0000
8.750 0.9424 0.05902 0.05060 0.0034 0.1580 1.0000
9.000 0.9335 0.06477 0.05674 0.0035 0.1594 1.0000
9.250 0.9206 0.07085 0.06307 0.0029 0.1614 1.0000
9.500 0.9091 0.07686 0.06922 0.0019 0.1633 1.0000
9.750 0.8993 0.08294 0.07541 0.0006 0.1660 1.0000
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Polar data table (+)
Polar graphs
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