RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Reynolds number: 200,000 Max Cl/Cd: 48.24 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bqm34-il-200000.txt Download as CSV file: xf-bqm34-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6171 0.07999 0.07656 -0.0175 1.0000 0.0586
-10.500 -0.8657 0.05794 0.05345 -0.0306 1.0000 0.0369
-10.250 -0.8792 0.05381 0.04916 -0.0288 1.0000 0.0365
-10.000 -0.8904 0.04997 0.04503 -0.0266 1.0000 0.0365
-9.750 -0.8962 0.04586 0.04061 -0.0245 1.0000 0.0362
-9.500 -0.8977 0.04192 0.03631 -0.0223 1.0000 0.0360
-9.250 -0.8946 0.03822 0.03220 -0.0201 1.0000 0.0360
-9.000 -0.8866 0.03502 0.02859 -0.0180 1.0000 0.0362
-8.750 -0.8747 0.03241 0.02556 -0.0160 1.0000 0.0367
-8.500 -0.8594 0.03061 0.02336 -0.0142 1.0000 0.0373
-8.250 -0.8431 0.02726 0.01986 -0.0132 1.0000 0.0391
-8.000 -0.8231 0.02610 0.01864 -0.0122 1.0000 0.0412
-7.750 -0.8025 0.02482 0.01719 -0.0110 1.0000 0.0435
-7.500 -0.7812 0.02351 0.01564 -0.0097 1.0000 0.0455
-7.250 -0.7605 0.02158 0.01362 -0.0086 1.0000 0.0481
-7.000 -0.7394 0.02070 0.01274 -0.0076 1.0000 0.0518
-6.750 -0.7175 0.01985 0.01177 -0.0064 1.0000 0.0555
-6.500 -0.6979 0.01847 0.01041 -0.0050 1.0000 0.0598
-6.250 -0.6770 0.01778 0.00971 -0.0038 1.0000 0.0655
-6.000 -0.6579 0.01674 0.00867 -0.0022 1.0000 0.0713
-5.750 -0.6375 0.01611 0.00802 -0.0008 1.0000 0.0793
-5.500 -0.6189 0.01527 0.00726 0.0007 1.0000 0.0894
-5.250 -0.5999 0.01453 0.00659 0.0023 1.0000 0.1034
-5.000 -0.5814 0.01380 0.00595 0.0040 1.0000 0.1242
-4.750 -0.5637 0.01303 0.00541 0.0056 1.0000 0.1575
-4.500 -0.5465 0.01226 0.00494 0.0073 1.0000 0.2103
-4.250 -0.5301 0.01151 0.00457 0.0091 1.0000 0.2825
-4.000 -0.5144 0.01084 0.00429 0.0111 1.0000 0.3657
-3.750 -0.4985 0.01033 0.00415 0.0132 1.0000 0.4476
-3.500 -0.4819 0.01000 0.00409 0.0153 1.0000 0.5157
-3.250 -0.4645 0.00982 0.00410 0.0173 1.0000 0.5703
-3.000 -0.4471 0.00972 0.00415 0.0193 1.0000 0.6148
-2.750 -0.4299 0.00969 0.00421 0.0213 1.0000 0.6522
-2.500 -0.4016 0.00970 0.00432 0.0211 0.9966 0.6890
-2.250 -0.3611 0.00973 0.00440 0.0185 0.9887 0.7246
-2.000 -0.3204 0.00974 0.00446 0.0160 0.9812 0.7549
-1.750 -0.2807 0.00971 0.00450 0.0139 0.9730 0.7812
-1.500 -0.2421 0.00968 0.00452 0.0120 0.9647 0.8053
-1.250 -0.2002 0.00965 0.00453 0.0095 0.9579 0.8276
-1.000 -0.1617 0.00962 0.00454 0.0077 0.9494 0.8490
-0.750 -0.1187 0.00960 0.00456 0.0053 0.9429 0.8677
-0.500 -0.0806 0.00959 0.00458 0.0038 0.9332 0.8851
-0.250 -0.0372 0.00957 0.00457 0.0013 0.9256 0.8996
0.000 0.0000 0.00957 0.00457 0.0000 0.9130 0.9130
0.250 0.0373 0.00957 0.00457 -0.0013 0.8995 0.9256
0.500 0.0806 0.00959 0.00458 -0.0038 0.8851 0.9332
0.750 0.1187 0.00960 0.00456 -0.0052 0.8678 0.9429
1.000 0.1617 0.00962 0.00454 -0.0077 0.8489 0.9494
1.250 0.2002 0.00965 0.00453 -0.0095 0.8274 0.9579
1.500 0.2420 0.00968 0.00452 -0.0119 0.8054 0.9647
1.750 0.2807 0.00971 0.00450 -0.0139 0.7811 0.9730
2.000 0.3204 0.00974 0.00446 -0.0160 0.7551 0.9812
2.250 0.3611 0.00973 0.00440 -0.0185 0.7245 0.9887
2.500 0.4017 0.00970 0.00431 -0.0211 0.6884 0.9967
2.750 0.4297 0.00969 0.00421 -0.0212 0.6518 1.0000
3.000 0.4470 0.00972 0.00414 -0.0193 0.6148 1.0000
3.250 0.4644 0.00982 0.00410 -0.0173 0.5706 1.0000
3.500 0.4817 0.01000 0.00409 -0.0152 0.5155 1.0000
3.750 0.4983 0.01033 0.00415 -0.0131 0.4477 1.0000
4.000 0.5143 0.01084 0.00429 -0.0111 0.3659 1.0000
4.250 0.5300 0.01151 0.00457 -0.0091 0.2826 1.0000
4.500 0.5463 0.01226 0.00494 -0.0073 0.2105 1.0000
4.750 0.5635 0.01302 0.00540 -0.0056 0.1575 1.0000
5.000 0.5813 0.01379 0.00595 -0.0039 0.1243 1.0000
5.250 0.5998 0.01453 0.00658 -0.0023 0.1034 1.0000
5.500 0.6188 0.01527 0.00726 -0.0007 0.0895 1.0000
5.750 0.6374 0.01611 0.00802 0.0009 0.0793 1.0000
6.000 0.6579 0.01674 0.00867 0.0022 0.0714 1.0000
6.250 0.6769 0.01778 0.00971 0.0038 0.0654 1.0000
6.500 0.6978 0.01847 0.01041 0.0051 0.0597 1.0000
6.750 0.7175 0.01986 0.01178 0.0064 0.0555 1.0000
7.000 0.7394 0.02070 0.01274 0.0076 0.0517 1.0000
7.250 0.7604 0.02158 0.01361 0.0086 0.0480 1.0000
7.500 0.7812 0.02352 0.01564 0.0097 0.0455 1.0000
7.750 0.8025 0.02481 0.01718 0.0110 0.0435 1.0000
8.000 0.8231 0.02608 0.01862 0.0122 0.0411 1.0000
8.250 0.8432 0.02725 0.01984 0.0132 0.0390 1.0000
8.500 0.8595 0.03053 0.02328 0.0142 0.0373 1.0000
8.750 0.8747 0.03242 0.02557 0.0160 0.0367 1.0000
9.000 0.8867 0.03504 0.02861 0.0180 0.0362 1.0000
9.250 0.8947 0.03823 0.03222 0.0201 0.0360 1.0000
9.500 0.8979 0.04193 0.03632 0.0223 0.0361 1.0000
9.750 0.8965 0.04591 0.04066 0.0244 0.0363 1.0000
10.000 0.8906 0.04995 0.04501 0.0266 0.0365 1.0000
10.250 0.8802 0.05389 0.04922 0.0286 0.0366 1.0000
10.500 0.8662 0.05782 0.05333 0.0306 0.0369 1.0000
10.750 0.8612 0.06183 0.05742 0.0318 0.0375 1.0000
11.000 0.8413 0.06501 0.06077 0.0329 0.0376 1.0000
11.250 0.6808 0.10439 0.10069 0.0069 0.0693 1.0000
11.500 0.6864 0.10894 0.10523 0.0089 0.0681 1.0000
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Polar data table (+)
Polar graphs
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