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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -0.9318 0.15893 0.15689 0.0281 1.0000 0.0065 -18.250 -0.9644 0.14613 0.14399 0.0211 1.0000 0.0066 -18.000 -0.9954 0.13441 0.13216 0.0146 1.0000 0.0065 -17.750 -1.0303 0.12242 0.12006 0.0080 1.0000 0.0064 -17.500 -1.0738 0.10923 0.10673 0.0008 1.0000 0.0064 -17.250 -1.1314 0.09393 0.09126 -0.0077 1.0000 0.0063 -17.000 -1.1788 0.08084 0.07799 -0.0151 1.0000 0.0063 -16.750 -1.2159 0.06991 0.06689 -0.0216 1.0000 0.0063 -16.500 -1.2417 0.06148 0.05829 -0.0268 1.0000 0.0063 -16.250 -1.2624 0.05442 0.05107 -0.0311 1.0000 0.0063 -16.000 -1.2765 0.04887 0.04536 -0.0342 1.0000 0.0063 -15.750 -1.2841 0.04465 0.04100 -0.0363 1.0000 0.0063 -15.500 -1.2934 0.04056 0.03677 -0.0378 1.0000 0.0063 -15.250 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0.00387 -0.0013 0.9844 0.0270 -5.750 -0.6296 0.00956 0.00362 -0.0023 0.9791 0.0298 -5.500 -0.5962 0.00928 0.00337 -0.0036 0.9732 0.0345 -5.250 -0.5623 0.00904 0.00314 -0.0050 0.9657 0.0393 -5.000 -0.5275 0.00878 0.00291 -0.0066 0.9560 0.0458 -4.750 -0.4949 0.00854 0.00269 -0.0077 0.9414 0.0540 -4.500 -0.4653 0.00834 0.00250 -0.0080 0.9224 0.0631 -4.250 -0.4386 0.00815 0.00231 -0.0078 0.9006 0.0756 -4.000 -0.4130 0.00800 0.00214 -0.0072 0.8789 0.0901 -3.750 -0.3876 0.00784 0.00198 -0.0067 0.8584 0.1072 -3.500 -0.3622 0.00767 0.00182 -0.0061 0.8393 0.1265 -3.250 -0.3368 0.00750 0.00169 -0.0056 0.8217 0.1511 -3.000 -0.3113 0.00732 0.00155 -0.0051 0.8055 0.1787 -2.750 -0.2858 0.00712 0.00143 -0.0046 0.7901 0.2104 -2.500 -0.2603 0.00691 0.00131 -0.0041 0.7754 0.2490 -2.250 -0.2349 0.00668 0.00120 -0.0037 0.7612 0.2919 -2.000 -0.2093 0.00647 0.00110 -0.0032 0.7473 0.3367 -1.750 -0.1837 0.00627 0.00101 -0.0028 0.7333 0.3831 -1.500 -0.1580 0.00608 0.00094 -0.0023 0.7193 0.4288 -1.250 -0.1320 0.00594 0.00089 -0.0019 0.7042 0.4687 -1.000 -0.1058 0.00583 0.00085 -0.0015 0.6878 0.5031 -0.750 -0.0794 0.00575 0.00082 -0.0011 0.6702 0.5346 -0.500 -0.0531 0.00571 0.00079 -0.0007 0.6501 0.5606 -0.250 -0.0266 0.00570 0.00078 -0.0004 0.6285 0.5849 0.000 0.0000 0.00569 0.00077 0.0000 0.6067 0.6065 0.250 0.0265 0.00570 0.00078 0.0004 0.5849 0.6286 0.500 0.0531 0.00571 0.00079 0.0007 0.5612 0.6502 0.750 0.0794 0.00576 0.00082 0.0011 0.5343 0.6698 1.000 0.1058 0.00583 0.00085 0.0015 0.5038 0.6879 1.250 0.1320 0.00593 0.00089 0.0019 0.4697 0.7041 1.500 0.1579 0.00608 0.00094 0.0023 0.4287 0.7192 1.750 0.1837 0.00627 0.00101 0.0028 0.3829 0.7334 2.000 0.2093 0.00647 0.00110 0.0032 0.3365 0.7473 2.250 0.2348 0.00669 0.00120 0.0037 0.2913 0.7613 2.500 0.2603 0.00691 0.00131 0.0041 0.2481 0.7755 2.750 0.2858 0.00712 0.00143 0.0046 0.2105 0.7901 3.000 0.3113 0.00732 0.00155 0.0051 0.1788 0.8054 3.500 0.3622 0.00767 0.00182 0.0061 0.1262 0.8394 3.750 0.3876 0.00784 0.00198 0.0067 0.1072 0.8584 4.000 0.4130 0.00800 0.00214 0.0072 0.0898 0.8788 4.250 0.4386 0.00816 0.00231 0.0078 0.0755 0.9006 4.500 0.4654 0.00834 0.00249 0.0080 0.0634 0.9224 4.750 0.4949 0.00854 0.00269 0.0077 0.0541 0.9414 5.000 0.5275 0.00878 0.00291 0.0066 0.0458 0.9560 5.250 0.5624 0.00904 0.00314 0.0050 0.0392 0.9658 5.500 0.5962 0.00928 0.00337 0.0036 0.0345 0.9733 5.750 0.6296 0.00956 0.00362 0.0023 0.0297 0.9792 6.000 0.6615 0.00980 0.00387 0.0013 0.0270 0.9844 6.250 0.6937 0.01010 0.00414 0.0003 0.0238 0.9886 6.500 0.7244 0.01036 0.00440 -0.0005 0.0218 0.9931 6.750 0.7555 0.01067 0.00470 -0.0014 0.0197 0.9970 7.000 0.7875 0.01097 0.00502 -0.0024 0.0183 0.9996 7.250 0.8124 0.01124 0.00530 -0.0019 0.0171 1.0000 7.500 0.8349 0.01154 0.00561 -0.0009 0.0160 1.0000 7.750 0.8571 0.01189 0.00597 0.0001 0.0148 1.0000 8.000 0.8799 0.01219 0.00630 0.0011 0.0141 1.0000 8.250 0.9026 0.01251 0.00663 0.0020 0.0133 1.0000 8.500 0.9250 0.01286 0.00700 0.0030 0.0125 1.0000 8.750 0.9467 0.01330 0.00745 0.0040 0.0116 1.0000 9.000 0.9691 0.01366 0.00785 0.0049 0.0112 1.0000 9.250 0.9914 0.01404 0.00828 0.0059 0.0108 1.0000 9.500 1.0135 0.01444 0.00872 0.0068 0.0104 1.0000 9.750 1.0354 0.01487 0.00918 0.0077 0.0100 1.0000 10.000 1.0570 0.01533 0.00968 0.0087 0.0096 1.0000 10.250 1.0781 0.01585 0.01024 0.0097 0.0092 1.0000 10.500 1.0981 0.01648 0.01092 0.0108 0.0088 1.0000 10.750 1.1186 0.01703 0.01153 0.0119 0.0086 1.0000 11.000 1.1391 0.01756 0.01213 0.0129 0.0085 1.0000 11.250 1.1589 0.01814 0.01278 0.0140 0.0083 1.0000 11.500 1.1783 0.01875 0.01346 0.0151 0.0081 1.0000 11.750 1.1968 0.01940 0.01418 0.0163 0.0080 1.0000 12.000 1.2151 0.02004 0.01489 0.0176 0.0078 1.0000 12.250 1.2319 0.02076 0.01569 0.0189 0.0076 1.0000 12.500 1.2485 0.02147 0.01646 0.0203 0.0074 1.0000 12.750 1.2632 0.02226 0.01734 0.0219 0.0073 1.0000 13.000 1.2771 0.02306 0.01822 0.0236 0.0072 1.0000 13.250 1.2877 0.02390 0.01913 0.0257 0.0070 1.0000 13.500 1.2940 0.02483 0.02013 0.0284 0.0069 1.0000 13.750 1.2992 0.02587 0.02127 0.0310 0.0069 1.0000 14.000 1.3011 0.02720 0.02270 0.0334 0.0067 1.0000 14.250 1.3011 0.02880 0.02441 0.0355 0.0065 1.0000 14.500 1.2985 0.03079 0.02652 0.0371 0.0065 1.0000 14.750 1.3002 0.03265 0.02849 0.0380 0.0064 1.0000 15.000 1.2997 0.03491 0.03087 0.0384 0.0064 1.0000 15.250 1.3011 0.03720 0.03328 0.0384 0.0063 1.0000 15.500 1.2950 0.04055 0.03676 0.0376 0.0063 1.0000 15.750 1.2909 0.04398 0.04032 0.0363 0.0063 1.0000 16.000 1.2783 0.04889 0.04539 0.0339 0.0063 1.0000 16.250 1.2662 0.05416 0.05080 0.0310 0.0062 1.0000 16.500 1.2516 0.06018 0.05697 0.0274 0.0062 1.0000 16.750 1.2232 0.06903 0.06599 0.0218 0.0063 1.0000 17.000 1.1794 0.08116 0.07832 0.0145 0.0063 1.0000 17.250 1.1356 0.09357 0.09090 0.0075 0.0063 1.0000 17.500 1.0803 0.10841 0.10591 -0.0006 0.0064 1.0000 17.750 1.0305 0.12282 0.12046 -0.0085 0.0064 1.0000 18.000 0.9947 0.13502 0.13278 -0.0152 0.0065 1.0000 18.250 0.9624 0.14705 0.14492 -0.0218 0.0065 1.0000 18.500 0.9314 0.15963 0.15761 -0.0287 0.0066 1.0000