RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Reynolds number: 50,000 Max Cl/Cd: 27.12 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bqm34-il-50000.txt Download as CSV file: xf-bqm34-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: RYAN BQM-34 FIREBEE WING 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5695 0.10544 0.09800 0.0182 1.0000 0.3480
-9.000 -0.7378 0.07622 0.06909 -0.0183 1.0000 0.1488
-8.750 -0.7812 0.06820 0.06071 -0.0204 1.0000 0.1361
-8.500 -0.7804 0.06336 0.05566 -0.0200 1.0000 0.1349
-8.250 -0.7806 0.05865 0.05069 -0.0193 1.0000 0.1343
-8.000 -0.7786 0.05413 0.04580 -0.0183 1.0000 0.1338
-7.750 -0.7735 0.04978 0.04105 -0.0170 1.0000 0.1333
-7.500 -0.7661 0.04579 0.03653 -0.0154 1.0000 0.1339
-7.250 -0.7537 0.04235 0.03272 -0.0140 1.0000 0.1378
-7.000 -0.7357 0.03966 0.02988 -0.0128 1.0000 0.1441
-6.750 -0.7199 0.03668 0.02628 -0.0110 1.0000 0.1489
-6.500 -0.6992 0.03429 0.02386 -0.0100 1.0000 0.1589
-6.250 -0.6781 0.03184 0.02111 -0.0087 1.0000 0.1691
-6.000 -0.6562 0.02983 0.01902 -0.0075 1.0000 0.1846
-5.750 -0.6332 0.02789 0.01703 -0.0063 1.0000 0.2041
-5.500 -0.6109 0.02608 0.01536 -0.0050 1.0000 0.2315
-5.250 -0.5897 0.02432 0.01378 -0.0034 1.0000 0.2713
-5.000 -0.5714 0.02257 0.01252 -0.0013 1.0000 0.3316
-4.750 -0.5581 0.02099 0.01173 0.0020 1.0000 0.4249
-4.500 -0.5479 0.02020 0.01169 0.0071 1.0000 0.5401
-4.250 -0.5360 0.02028 0.01215 0.0129 1.0000 0.6316
-4.000 -0.5202 0.02075 0.01272 0.0186 1.0000 0.6982
-3.750 -0.5015 0.02125 0.01320 0.0237 1.0000 0.7534
-3.500 -0.4733 0.02190 0.01372 0.0275 1.0000 0.8024
-3.250 -0.4188 0.02286 0.01435 0.0269 1.0000 0.8491
-3.000 -0.3202 0.02377 0.01471 0.0172 1.0000 0.8930
-2.750 -0.2207 0.02359 0.01405 0.0049 1.0000 0.9300
-2.500 -0.1420 0.02273 0.01287 -0.0053 1.0000 0.9616
-2.250 -0.0666 0.02148 0.01139 -0.0159 1.0000 0.9893
-2.000 -0.0276 0.02054 0.01035 -0.0202 1.0000 1.0000
-1.750 -0.0157 0.02000 0.00981 -0.0193 1.0000 1.0000
-1.500 -0.0047 0.01953 0.00935 -0.0181 1.0000 1.0000
-1.250 0.0049 0.01912 0.00897 -0.0165 1.0000 1.0000
-1.000 0.0123 0.01879 0.00867 -0.0146 1.0000 1.0000
-0.750 0.0167 0.01852 0.00845 -0.0121 1.0000 1.0000
-0.500 0.0169 0.01833 0.00832 -0.0090 1.0000 1.0000
-0.250 0.0112 0.01823 0.00826 -0.0049 1.0000 1.0000
0.000 0.0000 0.01820 0.00825 0.0000 1.0000 1.0000
0.250 -0.0112 0.01823 0.00826 0.0049 1.0000 1.0000
0.500 -0.0169 0.01833 0.00832 0.0090 1.0000 1.0000
0.750 -0.0166 0.01852 0.00845 0.0121 1.0000 1.0000
1.000 -0.0123 0.01878 0.00866 0.0146 1.0000 1.0000
1.250 -0.0048 0.01912 0.00896 0.0165 1.0000 1.0000
1.500 0.0048 0.01953 0.00934 0.0181 1.0000 1.0000
1.750 0.0158 0.02000 0.00980 0.0193 1.0000 1.0000
2.000 0.0277 0.02053 0.01034 0.0202 1.0000 1.0000
2.250 0.0667 0.02147 0.01138 0.0159 0.9893 1.0000
2.500 0.1420 0.02272 0.01286 0.0053 0.9616 1.0000
2.750 0.2212 0.02359 0.01404 -0.0050 0.9299 1.0000
3.000 0.3202 0.02376 0.01471 -0.0172 0.8930 1.0000
3.250 0.4191 0.02285 0.01435 -0.0269 0.8490 1.0000
3.500 0.4732 0.02190 0.01372 -0.0275 0.8025 1.0000
3.750 0.5014 0.02125 0.01320 -0.0237 0.7534 1.0000
4.000 0.5201 0.02075 0.01272 -0.0185 0.6981 1.0000
4.250 0.5359 0.02028 0.01214 -0.0128 0.6316 1.0000
4.500 0.5478 0.02020 0.01168 -0.0070 0.5404 1.0000
4.750 0.5580 0.02099 0.01173 -0.0020 0.4249 1.0000
5.000 0.5714 0.02257 0.01252 0.0013 0.3317 1.0000
5.250 0.5896 0.02432 0.01378 0.0034 0.2713 1.0000
5.500 0.6108 0.02608 0.01536 0.0050 0.2316 1.0000
5.750 0.6332 0.02789 0.01704 0.0063 0.2041 1.0000
6.000 0.6562 0.02983 0.01902 0.0075 0.1847 1.0000
6.250 0.6781 0.03184 0.02111 0.0087 0.1690 1.0000
6.500 0.6992 0.03428 0.02385 0.0100 0.1589 1.0000
6.750 0.7198 0.03668 0.02629 0.0110 0.1489 1.0000
7.000 0.7357 0.03967 0.02990 0.0128 0.1440 1.0000
7.250 0.7537 0.04237 0.03275 0.0140 0.1378 1.0000
7.500 0.7663 0.04580 0.03653 0.0154 0.1340 1.0000
7.750 0.7736 0.04978 0.04105 0.0170 0.1333 1.0000
8.000 0.7785 0.05414 0.04582 0.0183 0.1338 1.0000
8.250 0.7807 0.05868 0.05073 0.0193 0.1343 1.0000
8.500 0.7812 0.06337 0.05566 0.0200 0.1350 1.0000
8.750 0.7797 0.06823 0.06076 0.0204 0.1362 1.0000
9.000 0.6973 0.07929 0.07223 0.0149 0.1590 1.0000
9.250 0.5699 0.10548 0.09804 -0.0184 0.3481 1.0000
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Polar data table (+)
Polar graphs
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