RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Reynolds number: 50,000 Max Cl/Cd: 26.46 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bqm34-il-50000-n5.txt Download as CSV file: xf-bqm34-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7028 0.09736 0.08984 -0.0113 1.0000 0.0558
-11.000 -0.7180 0.08948 0.08198 -0.0164 1.0000 0.0554
-10.750 -0.7369 0.08214 0.07461 -0.0214 1.0000 0.0549
-10.500 -0.7605 0.07550 0.06794 -0.0255 1.0000 0.0545
-10.250 -0.7834 0.07023 0.06256 -0.0274 1.0000 0.0543
-10.000 -0.8045 0.06594 0.05812 -0.0271 1.0000 0.0541
-9.750 -0.8206 0.06177 0.05371 -0.0262 1.0000 0.0542
-9.500 -0.8311 0.05760 0.04921 -0.0250 1.0000 0.0545
-9.250 -0.8364 0.05356 0.04475 -0.0235 1.0000 0.0551
-9.000 -0.8374 0.04979 0.04042 -0.0218 1.0000 0.0562
-8.750 -0.8272 0.04709 0.03759 -0.0207 1.0000 0.0584
-8.500 -0.8145 0.04481 0.03514 -0.0196 1.0000 0.0611
-8.250 -0.8017 0.04211 0.03207 -0.0183 1.0000 0.0637
-8.000 -0.7864 0.03932 0.02880 -0.0170 1.0000 0.0664
-7.750 -0.7688 0.03709 0.02635 -0.0159 1.0000 0.0703
-7.500 -0.7495 0.03533 0.02447 -0.0149 1.0000 0.0751
-7.250 -0.7278 0.03334 0.02203 -0.0138 1.0000 0.0803
-7.000 -0.7074 0.03179 0.02056 -0.0130 1.0000 0.0867
-6.750 -0.6846 0.03021 0.01874 -0.0119 1.0000 0.0945
-6.500 -0.6639 0.02888 0.01744 -0.0109 1.0000 0.1038
-6.250 -0.6431 0.02757 0.01610 -0.0098 1.0000 0.1149
-6.000 -0.6230 0.02635 0.01487 -0.0085 1.0000 0.1294
-5.750 -0.6034 0.02516 0.01369 -0.0072 1.0000 0.1485
-5.500 -0.5852 0.02397 0.01265 -0.0059 1.0000 0.1733
-5.250 -0.5673 0.02279 0.01163 -0.0045 1.0000 0.2091
-5.000 -0.5508 0.02160 0.01077 -0.0029 1.0000 0.2577
-4.750 -0.5351 0.02052 0.01009 -0.0011 1.0000 0.3249
-4.500 -0.5196 0.01964 0.00966 0.0011 1.0000 0.4054
-4.000 -0.4877 0.01873 0.00931 0.0066 1.0000 0.5518
-3.750 -0.4703 0.01854 0.00924 0.0093 1.0000 0.6075
-3.500 -0.4520 0.01842 0.00918 0.0120 1.0000 0.6546
-3.250 -0.4335 0.01833 0.00907 0.0146 1.0000 0.6957
-3.000 -0.4136 0.01828 0.00902 0.0171 1.0000 0.7315
-2.750 -0.3930 0.01823 0.00896 0.0193 1.0000 0.7648
-2.500 -0.3706 0.01822 0.00891 0.0212 1.0000 0.7959
-2.250 -0.3450 0.01824 0.00887 0.0224 1.0000 0.8253
-2.000 -0.3155 0.01829 0.00885 0.0227 1.0000 0.8531
-1.750 -0.2833 0.01833 0.00881 0.0222 1.0000 0.8794
-1.500 -0.2409 0.01842 0.00878 0.0197 1.0000 0.9010
-1.250 -0.1988 0.01846 0.00872 0.0168 1.0000 0.9218
-1.000 -0.1548 0.01846 0.00864 0.0132 1.0000 0.9408
-0.750 -0.1069 0.01842 0.00853 0.0087 1.0000 0.9572
-0.500 -0.0608 0.01834 0.00841 0.0042 1.0000 0.9739
-0.250 -0.0156 0.01824 0.00829 -0.0003 1.0000 0.9915
0.000 0.0000 0.01820 0.00825 0.0000 1.0000 1.0000
0.250 0.0155 0.01824 0.00829 0.0003 0.9915 1.0000
0.500 0.0607 0.01834 0.00840 -0.0042 0.9739 1.0000
0.750 0.1068 0.01842 0.00852 -0.0087 0.9572 1.0000
1.000 0.1547 0.01846 0.00864 -0.0132 0.9408 1.0000
1.250 0.1988 0.01846 0.00872 -0.0168 0.9218 1.0000
1.500 0.2409 0.01842 0.00878 -0.0197 0.9011 1.0000
1.750 0.2832 0.01833 0.00881 -0.0222 0.8795 1.0000
2.000 0.3154 0.01829 0.00885 -0.0227 0.8531 1.0000
2.250 0.3449 0.01824 0.00887 -0.0224 0.8253 1.0000
2.500 0.3705 0.01822 0.00891 -0.0212 0.7959 1.0000
2.750 0.3930 0.01823 0.00896 -0.0193 0.7648 1.0000
3.000 0.4136 0.01828 0.00902 -0.0171 0.7316 1.0000
3.250 0.4334 0.01833 0.00910 -0.0146 0.6957 1.0000
3.500 0.4520 0.01842 0.00918 -0.0120 0.6546 1.0000
3.750 0.4702 0.01854 0.00924 -0.0093 0.6074 1.0000
4.000 0.4876 0.01873 0.00931 -0.0065 0.5517 1.0000
4.250 0.5041 0.01907 0.00942 -0.0037 0.4839 1.0000
4.500 0.5196 0.01964 0.00965 -0.0011 0.4054 1.0000
4.750 0.5350 0.02052 0.01009 0.0011 0.3247 1.0000
5.000 0.5508 0.02160 0.01077 0.0029 0.2578 1.0000
5.250 0.5673 0.02279 0.01164 0.0045 0.2092 1.0000
5.500 0.5852 0.02397 0.01265 0.0059 0.1735 1.0000
5.750 0.6034 0.02516 0.01369 0.0072 0.1484 1.0000
6.000 0.6231 0.02635 0.01487 0.0085 0.1295 1.0000
6.250 0.6432 0.02757 0.01610 0.0098 0.1148 1.0000
6.500 0.6640 0.02887 0.01743 0.0109 0.1038 1.0000
6.750 0.6846 0.03022 0.01875 0.0119 0.0944 1.0000
7.000 0.7074 0.03179 0.02056 0.0130 0.0866 1.0000
7.250 0.7279 0.03334 0.02204 0.0138 0.0802 1.0000
7.500 0.7496 0.03534 0.02448 0.0149 0.0752 1.0000
7.750 0.7689 0.03710 0.02636 0.0159 0.0703 1.0000
8.000 0.7865 0.03933 0.02881 0.0169 0.0664 1.0000
8.250 0.8018 0.04213 0.03209 0.0183 0.0637 1.0000
8.500 0.8147 0.04484 0.03516 0.0196 0.0611 1.0000
8.750 0.8275 0.04706 0.03754 0.0207 0.0583 1.0000
9.000 0.8376 0.04981 0.04045 0.0218 0.0562 1.0000
9.250 0.8365 0.05360 0.04479 0.0235 0.0551 1.0000
9.500 0.8312 0.05764 0.04924 0.0249 0.0545 1.0000
9.750 0.8211 0.06177 0.05371 0.0261 0.0542 1.0000
10.000 0.8048 0.06599 0.05817 0.0270 0.0541 1.0000
10.250 0.7839 0.07027 0.06259 0.0273 0.0543 1.0000
10.500 0.7617 0.07546 0.06790 0.0254 0.0546 1.0000
10.750 0.7375 0.08216 0.07464 0.0212 0.0549 1.0000
11.000 0.7187 0.08953 0.08202 0.0162 0.0554 1.0000
11.250 0.7041 0.09727 0.08975 0.0113 0.0558 1.0000
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Polar data table (+)
Polar graphs
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