RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Reynolds number: 200,000 Max Cl/Cd: 42.38 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bqm34-il-200000-n5.txt Download as CSV file: xf-bqm34-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.8762 0.07469 0.07058 -0.0204 1.0000 0.0168
-12.750 -0.9204 0.06280 0.05839 -0.0291 1.0000 0.0164
-12.500 -0.9576 0.05428 0.04952 -0.0338 1.0000 0.0160
-12.250 -0.9676 0.05067 0.04576 -0.0350 1.0000 0.0162
-12.000 -0.9831 0.04671 0.04155 -0.0351 1.0000 0.0162
-11.750 -0.9898 0.04421 0.03887 -0.0342 1.0000 0.0165
-11.500 -0.9970 0.04178 0.03623 -0.0324 1.0000 0.0169
-11.250 -1.0020 0.03963 0.03386 -0.0298 1.0000 0.0172
-11.000 -1.0036 0.03741 0.03138 -0.0272 1.0000 0.0176
-10.750 -0.9995 0.03524 0.02891 -0.0252 1.0000 0.0180
-10.500 -0.9923 0.03310 0.02646 -0.0232 1.0000 0.0184
-10.250 -0.9814 0.03122 0.02428 -0.0215 1.0000 0.0189
-10.000 -0.9687 0.02948 0.02240 -0.0200 1.0000 0.0193
-9.750 -0.9536 0.02821 0.02105 -0.0187 1.0000 0.0199
-9.500 -0.9371 0.02704 0.01978 -0.0174 1.0000 0.0206
-9.250 -0.9198 0.02589 0.01848 -0.0162 1.0000 0.0214
-9.000 -0.9016 0.02481 0.01725 -0.0150 1.0000 0.0225
-8.750 -0.8823 0.02383 0.01606 -0.0138 1.0000 0.0238
-8.500 -0.8646 0.02273 0.01496 -0.0126 1.0000 0.0251
-8.250 -0.8452 0.02190 0.01408 -0.0115 1.0000 0.0264
-8.000 -0.8255 0.02103 0.01310 -0.0103 1.0000 0.0279
-7.750 -0.8053 0.02024 0.01218 -0.0091 1.0000 0.0296
-7.500 -0.7863 0.01937 0.01131 -0.0078 1.0000 0.0316
-7.250 -0.7657 0.01873 0.01063 -0.0067 1.0000 0.0340
-7.000 -0.7451 0.01808 0.00988 -0.0055 1.0000 0.0365
-6.750 -0.7255 0.01735 0.00913 -0.0042 1.0000 0.0395
-6.500 -0.7047 0.01680 0.00856 -0.0030 1.0000 0.0432
-6.250 -0.6840 0.01624 0.00794 -0.0018 1.0000 0.0470
-6.000 -0.6638 0.01566 0.00737 -0.0005 1.0000 0.0521
-5.750 -0.6429 0.01518 0.00685 0.0007 1.0000 0.0582
-5.500 -0.6221 0.01469 0.00638 0.0019 1.0000 0.0659
-5.250 -0.6015 0.01421 0.00595 0.0032 1.0000 0.0759
-5.000 -0.5808 0.01377 0.00553 0.0044 1.0000 0.0887
-4.750 -0.5604 0.01334 0.00518 0.0057 1.0000 0.1058
-4.500 -0.5404 0.01291 0.00485 0.0070 1.0000 0.1278
-4.250 -0.5208 0.01249 0.00456 0.0083 1.0000 0.1562
-4.000 -0.4942 0.01203 0.00426 0.0082 0.9970 0.1954
-3.750 -0.4607 0.01148 0.00397 0.0065 0.9896 0.2520
-3.500 -0.4272 0.01092 0.00372 0.0048 0.9824 0.3214
-3.250 -0.3954 0.01041 0.00351 0.0037 0.9737 0.3953
-3.000 -0.3634 0.00999 0.00337 0.0026 0.9651 0.4655
-2.750 -0.3298 0.00969 0.00328 0.0014 0.9567 0.5243
-2.500 -0.2984 0.00946 0.00320 0.0008 0.9459 0.5709
-2.250 -0.2656 0.00928 0.00314 -0.0001 0.9357 0.6089
-2.000 -0.2318 0.00914 0.00308 -0.0011 0.9256 0.6415
-1.750 -0.2005 0.00903 0.00301 -0.0016 0.9127 0.6685
-1.500 -0.1694 0.00894 0.00296 -0.0019 0.8995 0.6930
-1.250 -0.1392 0.00886 0.00292 -0.0021 0.8856 0.7152
-1.000 -0.1100 0.00879 0.00288 -0.0020 0.8711 0.7370
-0.750 -0.0818 0.00874 0.00285 -0.0016 0.8560 0.7570
-0.500 -0.0542 0.00870 0.00283 -0.0011 0.8406 0.7753
-0.250 -0.0270 0.00868 0.00282 -0.0006 0.8249 0.7926
0.000 0.0000 0.00868 0.00281 0.0000 0.8090 0.8089
0.250 0.0270 0.00868 0.00282 0.0006 0.7925 0.8249
0.500 0.0542 0.00870 0.00283 0.0011 0.7754 0.8406
0.750 0.0818 0.00874 0.00285 0.0016 0.7571 0.8560
1.000 0.1100 0.00879 0.00288 0.0020 0.7370 0.8711
1.250 0.1392 0.00886 0.00292 0.0021 0.7150 0.8857
1.500 0.1694 0.00894 0.00296 0.0019 0.6929 0.8995
1.750 0.2005 0.00903 0.00301 0.0016 0.6687 0.9128
2.000 0.2317 0.00914 0.00307 0.0011 0.6416 0.9256
2.250 0.2656 0.00928 0.00314 0.0001 0.6091 0.9358
2.500 0.2984 0.00946 0.00320 -0.0008 0.5710 0.9459
2.750 0.3298 0.00969 0.00328 -0.0014 0.5240 0.9568
3.000 0.3633 0.01000 0.00337 -0.0026 0.4645 0.9651
3.250 0.3955 0.01041 0.00351 -0.0037 0.3959 0.9737
3.500 0.4271 0.01092 0.00372 -0.0048 0.3215 0.9825
3.750 0.4607 0.01148 0.00397 -0.0065 0.2521 0.9897
4.000 0.4942 0.01203 0.00426 -0.0082 0.1953 0.9971
4.250 0.5206 0.01249 0.00456 -0.0083 0.1561 1.0000
4.500 0.5403 0.01291 0.00485 -0.0070 0.1279 1.0000
4.750 0.5602 0.01334 0.00517 -0.0057 0.1056 1.0000
5.000 0.5807 0.01377 0.00553 -0.0044 0.0887 1.0000
5.250 0.6014 0.01421 0.00594 -0.0032 0.0759 1.0000
5.500 0.6220 0.01469 0.00638 -0.0019 0.0659 1.0000
5.750 0.6428 0.01518 0.00685 -0.0007 0.0582 1.0000
6.000 0.6637 0.01566 0.00737 0.0005 0.0522 1.0000
6.250 0.6840 0.01624 0.00794 0.0018 0.0470 1.0000
6.500 0.7046 0.01680 0.00856 0.0030 0.0432 1.0000
6.750 0.7255 0.01735 0.00914 0.0042 0.0395 1.0000
7.000 0.7451 0.01808 0.00988 0.0055 0.0365 1.0000
7.250 0.7657 0.01873 0.01063 0.0067 0.0340 1.0000
7.500 0.7863 0.01937 0.01131 0.0078 0.0317 1.0000
7.750 0.8054 0.02024 0.01218 0.0091 0.0296 1.0000
8.000 0.8256 0.02102 0.01309 0.0102 0.0278 1.0000
8.250 0.8453 0.02190 0.01407 0.0114 0.0264 1.0000
8.500 0.8648 0.02271 0.01494 0.0125 0.0250 1.0000
8.750 0.8825 0.02383 0.01607 0.0138 0.0238 1.0000
9.000 0.9017 0.02482 0.01726 0.0150 0.0225 1.0000
9.250 0.9200 0.02589 0.01848 0.0162 0.0214 1.0000
9.500 0.9373 0.02705 0.01979 0.0174 0.0206 1.0000
9.750 0.9538 0.02820 0.02104 0.0187 0.0199 1.0000
10.000 0.9690 0.02951 0.02243 0.0200 0.0194 1.0000
10.250 0.9817 0.03123 0.02428 0.0215 0.0189 1.0000
10.500 0.9927 0.03309 0.02644 0.0232 0.0185 1.0000
10.750 0.9999 0.03524 0.02890 0.0251 0.0180 1.0000
11.000 1.0040 0.03741 0.03139 0.0272 0.0176 1.0000
11.250 1.0028 0.03961 0.03384 0.0297 0.0172 1.0000
11.500 0.9981 0.04171 0.03616 0.0323 0.0168 1.0000
11.750 0.9911 0.04413 0.03879 0.0341 0.0165 1.0000
12.000 0.9836 0.04675 0.04159 0.0350 0.0163 1.0000
12.250 0.9692 0.05056 0.04564 0.0349 0.0162 1.0000
12.500 0.9631 0.05361 0.04880 0.0339 0.0158 1.0000
12.750 0.9364 0.06030 0.05578 0.0305 0.0160 1.0000
13.000 0.9099 0.06813 0.06385 0.0251 0.0160 1.0000
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