RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Reynolds number: 100,000 Max Cl/Cd: 34.85 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bqm34-il-100000-n5.txt Download as CSV file: xf-bqm34-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7445 0.09633 0.09094 -0.0084 1.0000 0.0298
-12.000 -0.7632 0.08717 0.08178 -0.0141 1.0000 0.0294
-11.750 -0.7897 0.07735 0.07188 -0.0213 1.0000 0.0289
-11.500 -0.8178 0.06915 0.06356 -0.0274 1.0000 0.0285
-11.250 -0.8432 0.06295 0.05717 -0.0309 1.0000 0.0283
-11.000 -0.8657 0.05818 0.05219 -0.0320 1.0000 0.0282
-10.750 -0.8851 0.05440 0.04817 -0.0311 1.0000 0.0283
-10.500 -0.9030 0.05097 0.04445 -0.0287 1.0000 0.0286
-10.250 -0.9132 0.04745 0.04052 -0.0265 1.0000 0.0292
-10.000 -0.9179 0.04410 0.03665 -0.0242 1.0000 0.0298
-9.750 -0.9103 0.04171 0.03411 -0.0228 1.0000 0.0307
-9.500 -0.8997 0.03968 0.03191 -0.0215 1.0000 0.0316
-9.250 -0.8880 0.03750 0.02949 -0.0201 1.0000 0.0325
-9.000 -0.8745 0.03533 0.02703 -0.0187 1.0000 0.0336
-8.750 -0.8590 0.03330 0.02470 -0.0173 1.0000 0.0351
-8.500 -0.8420 0.03154 0.02251 -0.0159 1.0000 0.0373
-8.250 -0.8240 0.02991 0.02089 -0.0150 1.0000 0.0392
-8.000 -0.8049 0.02854 0.01942 -0.0139 1.0000 0.0412
-7.750 -0.7849 0.02715 0.01785 -0.0128 1.0000 0.0438
-7.500 -0.7648 0.02586 0.01638 -0.0116 1.0000 0.0470
-7.250 -0.7455 0.02474 0.01528 -0.0105 1.0000 0.0502
-7.000 -0.7253 0.02366 0.01408 -0.0093 1.0000 0.0539
-6.750 -0.7058 0.02262 0.01298 -0.0081 1.0000 0.0586
-6.500 -0.6862 0.02174 0.01209 -0.0068 1.0000 0.0640
-6.250 -0.6668 0.02083 0.01113 -0.0054 1.0000 0.0702
-6.000 -0.6472 0.02005 0.01031 -0.0041 1.0000 0.0784
-5.750 -0.6282 0.01922 0.00952 -0.0027 1.0000 0.0877
-5.500 -0.6089 0.01847 0.00882 -0.0013 1.0000 0.1007
-5.250 -0.5895 0.01776 0.00816 0.0001 1.0000 0.1180
-5.000 -0.5705 0.01705 0.00756 0.0015 1.0000 0.1417
-4.750 -0.5515 0.01636 0.00703 0.0029 1.0000 0.1745
-4.500 -0.5328 0.01567 0.00656 0.0043 1.0000 0.2175
-4.250 -0.5148 0.01498 0.00616 0.0058 1.0000 0.2734
-4.000 -0.4973 0.01433 0.00581 0.0075 1.0000 0.3397
-3.750 -0.4800 0.01377 0.00559 0.0093 1.0000 0.4115
-3.500 -0.4623 0.01335 0.00546 0.0113 1.0000 0.4789
-3.250 -0.4443 0.01306 0.00539 0.0132 1.0000 0.5371
-3.000 -0.4258 0.01288 0.00533 0.0152 1.0000 0.5860
-2.750 -0.4073 0.01275 0.00533 0.0171 1.0000 0.6267
-2.500 -0.3818 0.01269 0.00534 0.0176 0.9964 0.6652
-2.250 -0.3456 0.01266 0.00535 0.0161 0.9869 0.7012
-2.000 -0.3096 0.01264 0.00536 0.0146 0.9774 0.7322
-1.750 -0.2722 0.01264 0.00539 0.0130 0.9686 0.7607
-1.500 -0.2358 0.01263 0.00539 0.0116 0.9589 0.7874
-1.250 -0.1984 0.01264 0.00542 0.0101 0.9496 0.8110
-1.000 -0.1583 0.01264 0.00543 0.0079 0.9412 0.8330
-0.750 -0.1209 0.01265 0.00545 0.0064 0.9301 0.8512
-0.500 -0.0811 0.01266 0.00546 0.0044 0.9196 0.8677
-0.250 -0.0393 0.01266 0.00546 0.0020 0.9094 0.8825
0.000 0.0000 0.01266 0.00546 0.0000 0.8964 0.8964
0.250 0.0393 0.01266 0.00545 -0.0020 0.8824 0.9094
0.500 0.0811 0.01266 0.00546 -0.0044 0.8677 0.9196
0.750 0.1209 0.01265 0.00545 -0.0064 0.8512 0.9301
1.000 0.1583 0.01264 0.00543 -0.0079 0.8330 0.9413
1.250 0.1983 0.01264 0.00542 -0.0100 0.8110 0.9496
1.500 0.2357 0.01263 0.00539 -0.0115 0.7873 0.9589
1.750 0.2722 0.01264 0.00539 -0.0130 0.7606 0.9687
2.000 0.3096 0.01264 0.00536 -0.0146 0.7324 0.9775
2.250 0.3456 0.01266 0.00535 -0.0161 0.7013 0.9869
2.500 0.3818 0.01269 0.00533 -0.0176 0.6653 0.9965
2.750 0.4072 0.01275 0.00533 -0.0171 0.6271 1.0000
3.000 0.4257 0.01288 0.00533 -0.0152 0.5863 1.0000
3.250 0.4441 0.01306 0.00539 -0.0132 0.5369 1.0000
3.500 0.4622 0.01335 0.00546 -0.0112 0.4786 1.0000
3.750 0.4799 0.01377 0.00559 -0.0093 0.4113 1.0000
4.000 0.4972 0.01433 0.00581 -0.0075 0.3397 1.0000
4.250 0.5147 0.01498 0.00616 -0.0058 0.2735 1.0000
4.500 0.5327 0.01567 0.00656 -0.0043 0.2176 1.0000
4.750 0.5514 0.01636 0.00703 -0.0029 0.1745 1.0000
5.000 0.5704 0.01705 0.00756 -0.0015 0.1418 1.0000
5.250 0.5895 0.01776 0.00816 -0.0001 0.1180 1.0000
5.500 0.6088 0.01847 0.00882 0.0013 0.1007 1.0000
5.750 0.6282 0.01922 0.00952 0.0027 0.0876 1.0000
6.000 0.6472 0.02004 0.01031 0.0041 0.0784 1.0000
6.250 0.6668 0.02083 0.01112 0.0054 0.0700 1.0000
6.500 0.6862 0.02174 0.01208 0.0068 0.0640 1.0000
6.750 0.7058 0.02262 0.01298 0.0081 0.0585 1.0000
7.000 0.7253 0.02367 0.01409 0.0093 0.0539 1.0000
7.250 0.7455 0.02475 0.01529 0.0105 0.0502 1.0000
7.500 0.7649 0.02586 0.01638 0.0116 0.0471 1.0000
7.750 0.7850 0.02715 0.01785 0.0128 0.0438 1.0000
8.000 0.8049 0.02854 0.01942 0.0139 0.0412 1.0000
8.250 0.8241 0.02991 0.02088 0.0149 0.0392 1.0000
8.500 0.8421 0.03153 0.02250 0.0159 0.0373 1.0000
8.750 0.8591 0.03331 0.02471 0.0173 0.0351 1.0000
9.000 0.8746 0.03533 0.02704 0.0186 0.0336 1.0000
9.250 0.8882 0.03750 0.02949 0.0200 0.0325 1.0000
9.500 0.8999 0.03969 0.03192 0.0215 0.0316 1.0000
9.750 0.9106 0.04169 0.03409 0.0228 0.0307 1.0000
10.000 0.9186 0.04413 0.03666 0.0241 0.0299 1.0000
10.250 0.9138 0.04744 0.04051 0.0264 0.0292 1.0000
10.500 0.9040 0.05094 0.04441 0.0286 0.0287 1.0000
10.750 0.8858 0.05438 0.04815 0.0310 0.0283 1.0000
11.000 0.8663 0.05819 0.05220 0.0320 0.0282 1.0000
11.250 0.8446 0.06291 0.05712 0.0308 0.0284 1.0000
11.500 0.8188 0.06915 0.06355 0.0273 0.0286 1.0000
11.750 0.7920 0.07709 0.07160 0.0215 0.0290 1.0000
12.000 0.7668 0.08651 0.08110 0.0145 0.0294 1.0000
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Polar data table (+)
Polar graphs
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