RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Reynolds number: 100,000 Max Cl/Cd: 38.37 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bqm34-il-100000.txt Download as CSV file: xf-bqm34-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5878 0.07902 0.07422 -0.0149 1.0000 0.1111
-9.500 -0.7997 0.06613 0.06062 -0.0256 1.0000 0.0794
-9.250 -0.8011 0.06129 0.05570 -0.0250 1.0000 0.0775
-9.000 -0.8120 0.05592 0.05005 -0.0239 1.0000 0.0744
-8.750 -0.8393 0.04962 0.04256 -0.0201 1.0000 0.0681
-8.500 -0.8318 0.04508 0.03771 -0.0187 1.0000 0.0676
-8.250 -0.8231 0.04133 0.03353 -0.0168 1.0000 0.0677
-8.000 -0.8127 0.03778 0.02952 -0.0150 1.0000 0.0688
-7.750 -0.7946 0.03519 0.02696 -0.0143 1.0000 0.0722
-7.500 -0.7769 0.03292 0.02442 -0.0128 1.0000 0.0750
-7.250 -0.7582 0.03054 0.02160 -0.0112 1.0000 0.0775
-7.000 -0.7387 0.02845 0.01911 -0.0097 1.0000 0.0818
-6.750 -0.7167 0.02668 0.01738 -0.0089 1.0000 0.0874
-6.500 -0.6940 0.02520 0.01558 -0.0076 1.0000 0.0933
-6.250 -0.6718 0.02354 0.01405 -0.0067 1.0000 0.1016
-6.000 -0.6492 0.02206 0.01250 -0.0056 1.0000 0.1109
-5.750 -0.6279 0.02087 0.01134 -0.0043 1.0000 0.1239
-5.500 -0.6077 0.01966 0.01026 -0.0029 1.0000 0.1397
-5.250 -0.5885 0.01857 0.00930 -0.0013 1.0000 0.1634
-5.000 -0.5717 0.01733 0.00836 0.0006 1.0000 0.1974
-4.750 -0.5570 0.01604 0.00753 0.0027 1.0000 0.2560
-4.500 -0.5448 0.01474 0.00693 0.0054 1.0000 0.3535
-4.250 -0.5323 0.01388 0.00668 0.0083 1.0000 0.4676
-4.000 -0.5171 0.01348 0.00662 0.0113 1.0000 0.5538
-3.750 -0.5006 0.01331 0.00662 0.0141 1.0000 0.6165
-3.500 -0.4835 0.01325 0.00667 0.0169 1.0000 0.6650
-3.250 -0.4665 0.01323 0.00672 0.0198 1.0000 0.7064
-3.000 -0.4497 0.01323 0.00676 0.0227 1.0000 0.7425
-2.750 -0.4331 0.01326 0.00683 0.0257 1.0000 0.7752
-2.500 -0.4165 0.01330 0.00690 0.0287 1.0000 0.8062
-2.250 -0.3992 0.01339 0.00701 0.0315 1.0000 0.8363
-2.000 -0.3791 0.01353 0.00712 0.0338 1.0000 0.8657
-1.750 -0.3528 0.01373 0.00730 0.0347 1.0000 0.8946
-1.500 -0.3066 0.01412 0.00761 0.0320 1.0000 0.9187
-1.250 -0.2533 0.01449 0.00787 0.0275 1.0000 0.9410
-1.000 -0.1852 0.01480 0.00807 0.0199 1.0000 0.9562
-0.750 -0.1208 0.01491 0.00811 0.0125 1.0000 0.9703
-0.500 -0.0585 0.01488 0.00803 0.0051 1.0000 0.9835
-0.250 0.0037 0.01473 0.00785 -0.0026 1.0000 0.9961
0.000 0.0000 0.01470 0.00783 0.0000 1.0000 1.0000
0.250 -0.0036 0.01473 0.00785 0.0026 0.9961 1.0000
0.500 0.0584 0.01488 0.00803 -0.0051 0.9835 1.0000
0.750 0.1206 0.01491 0.00810 -0.0124 0.9703 1.0000
1.000 0.1850 0.01480 0.00807 -0.0198 0.9563 1.0000
1.250 0.2534 0.01448 0.00787 -0.0275 0.9410 1.0000
1.500 0.3067 0.01411 0.00761 -0.0320 0.9185 1.0000
1.750 0.3526 0.01373 0.00730 -0.0347 0.8947 1.0000
2.000 0.3790 0.01353 0.00712 -0.0338 0.8658 1.0000
2.250 0.3991 0.01339 0.00700 -0.0315 0.8363 1.0000
2.500 0.4164 0.01330 0.00690 -0.0287 0.8062 1.0000
2.750 0.4330 0.01326 0.00683 -0.0257 0.7753 1.0000
3.000 0.4496 0.01323 0.00676 -0.0227 0.7425 1.0000
3.250 0.4664 0.01323 0.00672 -0.0198 0.7064 1.0000
3.500 0.4833 0.01324 0.00667 -0.0169 0.6650 1.0000
3.750 0.5004 0.01331 0.00662 -0.0141 0.6164 1.0000
4.000 0.5170 0.01348 0.00662 -0.0112 0.5539 1.0000
4.250 0.5322 0.01387 0.00668 -0.0083 0.4677 1.0000
4.500 0.5447 0.01474 0.00693 -0.0053 0.3539 1.0000
4.750 0.5569 0.01604 0.00753 -0.0027 0.2560 1.0000
5.000 0.5716 0.01733 0.00836 -0.0005 0.1975 1.0000
5.250 0.5885 0.01856 0.00929 0.0013 0.1633 1.0000
5.500 0.6076 0.01965 0.01025 0.0029 0.1397 1.0000
5.750 0.6279 0.02087 0.01134 0.0044 0.1238 1.0000
6.000 0.6492 0.02206 0.01251 0.0056 0.1109 1.0000
6.250 0.6718 0.02355 0.01406 0.0067 0.1017 1.0000
6.500 0.6940 0.02520 0.01558 0.0076 0.0933 1.0000
6.750 0.7167 0.02669 0.01738 0.0089 0.0874 1.0000
7.000 0.7386 0.02847 0.01912 0.0097 0.0818 1.0000
7.250 0.7582 0.03054 0.02161 0.0112 0.0775 1.0000
7.500 0.7769 0.03293 0.02442 0.0128 0.0751 1.0000
7.750 0.7947 0.03518 0.02695 0.0143 0.0722 1.0000
8.000 0.8126 0.03791 0.02964 0.0149 0.0686 1.0000
8.250 0.8231 0.04134 0.03354 0.0168 0.0676 1.0000
8.500 0.8319 0.04507 0.03771 0.0187 0.0676 1.0000
8.750 0.8393 0.04963 0.04257 0.0201 0.0681 1.0000
9.000 0.8120 0.05596 0.05010 0.0239 0.0744 1.0000
9.250 0.8012 0.06135 0.05576 0.0250 0.0775 1.0000
9.500 0.8017 0.06620 0.06067 0.0255 0.0795 1.0000
9.750 0.6296 0.09815 0.09298 0.0002 0.1593 1.0000
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Polar data table (+)
Polar graphs
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