RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RYAN BQM-34 FIREBEE WING AIRFOIL (bqm34-il) Reynolds number: 1,000,000 Max Cl/Cd: 70.84 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bqm34-il-1000000.txt Download as CSV file: xf-bqm34-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.500 -1.0296 0.09982 0.09752 -0.0043 1.0000 0.0092
-16.250 -1.0652 0.08820 0.08574 -0.0111 1.0000 0.0091
-16.000 -1.0935 0.07849 0.07587 -0.0169 1.0000 0.0091
-15.750 -1.1103 0.07121 0.06845 -0.0215 1.0000 0.0090
-15.500 -1.1291 0.06391 0.06100 -0.0261 1.0000 0.0090
-15.250 -1.1385 0.05852 0.05549 -0.0295 1.0000 0.0089
-15.000 -1.1586 0.05190 0.04869 -0.0334 1.0000 0.0090
-14.750 -1.1817 0.04551 0.04211 -0.0366 1.0000 0.0091
-14.500 -1.1883 0.04179 0.03825 -0.0379 1.0000 0.0091
-14.250 -1.1987 0.03799 0.03429 -0.0387 1.0000 0.0091
-14.000 -1.2052 0.03502 0.03120 -0.0386 1.0000 0.0093
-13.750 -1.2093 0.03255 0.02859 -0.0378 1.0000 0.0094
-13.500 -1.2101 0.03062 0.02655 -0.0364 1.0000 0.0095
-13.250 -1.2065 0.02924 0.02508 -0.0348 1.0000 0.0096
-13.000 -1.2002 0.02818 0.02397 -0.0330 1.0000 0.0098
-12.750 -1.1970 0.02694 0.02263 -0.0304 1.0000 0.0100
-12.500 -1.1921 0.02591 0.02150 -0.0276 1.0000 0.0100
-12.250 -1.1834 0.02505 0.02056 -0.0252 1.0000 0.0103
-12.000 -1.1722 0.02401 0.01941 -0.0233 1.0000 0.0104
-11.750 -1.1583 0.02312 0.01842 -0.0216 1.0000 0.0107
-11.500 -1.1438 0.02219 0.01738 -0.0200 1.0000 0.0109
-11.250 -1.1278 0.02133 0.01643 -0.0185 1.0000 0.0111
-11.000 -1.1115 0.02046 0.01546 -0.0170 1.0000 0.0113
-10.750 -1.0931 0.01976 0.01467 -0.0157 1.0000 0.0114
-10.500 -1.0755 0.01893 0.01375 -0.0143 1.0000 0.0116
-10.250 -1.0630 0.01753 0.01222 -0.0122 1.0000 0.0121
-10.000 -1.0445 0.01677 0.01141 -0.0109 1.0000 0.0125
-9.750 -1.0241 0.01619 0.01079 -0.0098 1.0000 0.0129
-9.500 -1.0033 0.01566 0.01021 -0.0087 1.0000 0.0134
-9.250 -0.9820 0.01516 0.00966 -0.0076 1.0000 0.0139
-9.000 -0.9605 0.01470 0.00914 -0.0066 1.0000 0.0144
-8.750 -0.9382 0.01433 0.00872 -0.0056 1.0000 0.0148
-8.500 -0.9202 0.01348 0.00781 -0.0040 1.0000 0.0159
-8.250 -0.8984 0.01307 0.00739 -0.0030 1.0000 0.0169
-8.000 -0.8758 0.01273 0.00703 -0.0020 1.0000 0.0179
-7.750 -0.8528 0.01246 0.00672 -0.0011 1.0000 0.0188
-7.500 -0.8327 0.01187 0.00609 0.0003 1.0000 0.0204
-7.250 -0.8107 0.01152 0.00574 0.0014 1.0000 0.0218
-7.000 -0.7882 0.01124 0.00545 0.0024 1.0000 0.0232
-6.750 -0.7667 0.01087 0.00504 0.0037 1.0000 0.0250
-6.500 -0.7454 0.01052 0.00471 0.0049 1.0000 0.0274
-6.250 -0.7233 0.01029 0.00447 0.0060 1.0000 0.0294
-6.000 -0.7024 0.00996 0.00414 0.0074 1.0000 0.0326
-5.750 -0.6790 0.00971 0.00390 0.0082 0.9998 0.0361
-5.500 -0.6439 0.00939 0.00360 0.0065 0.9976 0.0419
-5.250 -0.6084 0.00911 0.00336 0.0047 0.9951 0.0490
-5.000 -0.5744 0.00881 0.00311 0.0033 0.9921 0.0589
-4.750 -0.5406 0.00848 0.00286 0.0019 0.9883 0.0742
-4.500 -0.5054 0.00817 0.00265 0.0001 0.9851 0.0933
-4.250 -0.4718 0.00783 0.00243 -0.0013 0.9809 0.1201
-4.000 -0.4386 0.00748 0.00222 -0.0025 0.9750 0.1529
-3.500 -0.3718 0.00674 0.00183 -0.0052 0.9595 0.2393
-3.250 -0.3407 0.00635 0.00165 -0.0061 0.9469 0.2964
-3.000 -0.3122 0.00599 0.00149 -0.0063 0.9306 0.3550
-2.750 -0.2860 0.00571 0.00136 -0.0059 0.9116 0.4108
-2.500 -0.2609 0.00549 0.00125 -0.0052 0.8918 0.4617
-2.250 -0.2358 0.00532 0.00118 -0.0045 0.8721 0.5050
-2.000 -0.2103 0.00522 0.00111 -0.0039 0.8533 0.5410
-1.750 -0.1846 0.00513 0.00106 -0.0033 0.8355 0.5725
-1.500 -0.1587 0.00507 0.00102 -0.0027 0.8188 0.6009
-1.250 -0.1327 0.00502 0.00099 -0.0022 0.8024 0.6255
-1.000 -0.1063 0.00500 0.00097 -0.0017 0.7862 0.6473
-0.750 -0.0799 0.00497 0.00095 -0.0013 0.7702 0.6675
-0.500 -0.0534 0.00496 0.00094 -0.0008 0.7535 0.6860
-0.250 -0.0267 0.00495 0.00093 -0.0004 0.7365 0.7034
0.000 0.0000 0.00495 0.00093 0.0000 0.7200 0.7199
0.250 0.0267 0.00495 0.00093 0.0004 0.7034 0.7366
0.500 0.0533 0.00496 0.00094 0.0008 0.6862 0.7536
0.750 0.0799 0.00497 0.00095 0.0013 0.6674 0.7700
1.000 0.1062 0.00500 0.00097 0.0017 0.6475 0.7862
1.250 0.1327 0.00502 0.00099 0.0022 0.6258 0.8023
1.500 0.1587 0.00507 0.00102 0.0027 0.6009 0.8187
1.750 0.1846 0.00513 0.00106 0.0033 0.5724 0.8356
2.250 0.2357 0.00532 0.00118 0.0046 0.5047 0.8722
2.500 0.2608 0.00549 0.00125 0.0052 0.4611 0.8919
2.750 0.2860 0.00571 0.00136 0.0059 0.4109 0.9117
3.000 0.3122 0.00599 0.00149 0.0063 0.3551 0.9306
3.250 0.3407 0.00635 0.00165 0.0061 0.2954 0.9470
3.500 0.3718 0.00674 0.00183 0.0052 0.2391 0.9596
4.000 0.4386 0.00747 0.00222 0.0026 0.1528 0.9751
4.250 0.4717 0.00783 0.00243 0.0013 0.1201 0.9810
4.500 0.5054 0.00817 0.00265 -0.0001 0.0933 0.9851
4.750 0.5406 0.00848 0.00286 -0.0019 0.0740 0.9884
5.000 0.5744 0.00881 0.00311 -0.0033 0.0589 0.9921
5.250 0.6086 0.00911 0.00336 -0.0048 0.0491 0.9952
5.500 0.6440 0.00939 0.00360 -0.0065 0.0418 0.9977
5.750 0.6791 0.00971 0.00390 -0.0082 0.0361 0.9998
6.000 0.7023 0.00996 0.00414 -0.0074 0.0327 1.0000
6.250 0.7231 0.01029 0.00447 -0.0060 0.0294 1.0000
6.500 0.7452 0.01052 0.00471 -0.0049 0.0274 1.0000
6.750 0.7666 0.01087 0.00505 -0.0036 0.0250 1.0000
7.000 0.7881 0.01124 0.00545 -0.0024 0.0232 1.0000
7.250 0.8106 0.01152 0.00574 -0.0014 0.0218 1.0000
7.500 0.8327 0.01186 0.00608 -0.0003 0.0204 1.0000
7.750 0.8528 0.01245 0.00672 0.0011 0.0188 1.0000
8.000 0.8757 0.01273 0.00703 0.0020 0.0178 1.0000
8.250 0.8984 0.01306 0.00738 0.0030 0.0168 1.0000
8.500 0.9202 0.01347 0.00780 0.0040 0.0159 1.0000
8.750 0.9381 0.01433 0.00872 0.0057 0.0148 1.0000
9.000 0.9604 0.01471 0.00916 0.0066 0.0145 1.0000
9.250 0.9820 0.01517 0.00967 0.0076 0.0139 1.0000
9.500 1.0032 0.01568 0.01023 0.0087 0.0134 1.0000
9.750 1.0242 0.01620 0.01079 0.0098 0.0129 1.0000
10.000 1.0447 0.01676 0.01140 0.0109 0.0125 1.0000
10.250 1.0633 0.01751 0.01220 0.0122 0.0121 1.0000
10.500 1.0763 0.01886 0.01367 0.0142 0.0116 1.0000
10.750 1.0928 0.01981 0.01473 0.0157 0.0114 1.0000
11.000 1.1115 0.02048 0.01548 0.0170 0.0113 1.0000
11.250 1.1282 0.02132 0.01642 0.0184 0.0111 1.0000
11.500 1.1446 0.02214 0.01733 0.0199 0.0109 1.0000
11.750 1.1588 0.02310 0.01840 0.0215 0.0107 1.0000
12.000 1.1730 0.02397 0.01937 0.0232 0.0104 1.0000
12.250 1.1850 0.02494 0.02043 0.0250 0.0102 1.0000
12.500 1.1935 0.02585 0.02143 0.0274 0.0100 1.0000
12.750 1.1988 0.02685 0.02252 0.0302 0.0099 1.0000
13.000 1.2049 0.02785 0.02359 0.0325 0.0097 1.0000
13.250 1.2090 0.02909 0.02491 0.0345 0.0095 1.0000
13.500 1.2109 0.03060 0.02650 0.0363 0.0093 1.0000
13.750 1.2081 0.03276 0.02883 0.0377 0.0094 1.0000
14.000 1.2042 0.03519 0.03135 0.0384 0.0092 1.0000
14.250 1.1994 0.03803 0.03433 0.0385 0.0091 1.0000
14.500 1.1877 0.04200 0.03847 0.0377 0.0090 1.0000
14.750 1.1805 0.04586 0.04247 0.0362 0.0091 1.0000
15.000 1.1707 0.05040 0.04716 0.0340 0.0091 1.0000
15.250 1.1376 0.05892 0.05591 0.0290 0.0089 1.0000
15.500 1.1320 0.06374 0.06083 0.0259 0.0090 1.0000
15.750 1.1146 0.07077 0.06801 0.0214 0.0090 1.0000
16.000 1.0879 0.07990 0.07730 0.0157 0.0090 1.0000
16.250 1.0635 0.08893 0.08647 0.0103 0.0091 1.0000
16.500 1.0397 0.09810 0.09576 0.0050 0.0091 1.0000
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Polar data table (+)
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