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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.750 -0.9473 0.06937 0.06635 -0.0260 1.0000 0.0152 -13.500 -0.9680 0.06219 0.05896 -0.0312 1.0000 0.0151 -13.250 -0.9842 0.05670 0.05330 -0.0347 1.0000 0.0150 -13.000 -1.0117 0.05039 0.04678 -0.0374 1.0000 0.0152 -12.750 -1.0279 0.04625 0.04243 -0.0382 1.0000 0.0152 -12.500 -1.0356 0.04354 0.03953 -0.0377 1.0000 0.0151 -12.250 -1.0538 0.03986 0.03563 -0.0361 1.0000 0.0152 -12.000 -1.0624 0.03742 0.03299 -0.0335 1.0000 0.0152 -11.750 -1.0701 0.03500 0.03039 -0.0303 1.0000 0.0154 -11.500 -1.0699 0.03303 0.02827 -0.0276 1.0000 0.0156 -11.250 -1.0627 0.03143 0.02654 -0.0256 1.0000 0.0158 -11.000 -1.0537 0.02976 0.02471 -0.0237 1.0000 0.0160 -10.750 -1.0418 0.02836 0.02317 -0.0220 1.0000 0.0163 -10.500 -1.0281 0.02704 0.02169 -0.0205 1.0000 0.0167 -10.250 -1.0134 0.02565 0.02015 -0.0189 1.0000 0.0171 -10.000 -0.9970 0.02444 0.01880 -0.0175 1.0000 0.0176 -9.750 -0.9800 0.02322 0.01742 -0.0161 1.0000 0.0181 -9.500 -0.9616 0.02217 0.01622 -0.0148 1.0000 0.0186 -9.250 -0.9431 0.02109 0.01499 -0.0135 1.0000 0.0191 -9.000 -0.9275 0.01955 0.01339 -0.0119 1.0000 0.0201 -8.750 -0.9071 0.01892 0.01274 -0.0109 1.0000 0.0210 -8.500 -0.8866 0.01825 0.01201 -0.0097 1.0000 0.0221 -8.250 -0.8658 0.01759 0.01126 -0.0085 1.0000 0.0232 -8.000 -0.8450 0.01694 0.01052 -0.0073 1.0000 0.0240 -7.750 -0.8287 0.01576 0.00931 -0.0055 1.0000 0.0257 -7.500 -0.8077 0.01524 0.00877 -0.0044 1.0000 0.0273 -7.250 -0.7862 0.01477 0.00825 -0.0032 1.0000 0.0290 -7.000 -0.7667 0.01408 0.00751 -0.0017 1.0000 0.0312 -6.750 -0.7459 0.01357 0.00701 -0.0005 1.0000 0.0338 -6.500 -0.7241 0.01320 0.00660 0.0006 1.0000 0.0364 -6.250 -0.7046 0.01258 0.00596 0.0022 1.0000 0.0398 -6.000 -0.6832 0.01221 0.00560 0.0034 1.0000 0.0439 -5.750 -0.6626 0.01177 0.00514 0.0047 1.0000 0.0486 -5.500 -0.6418 0.01139 0.00478 0.0061 1.0000 0.0546 -5.250 -0.6218 0.01098 0.00441 0.0075 1.0000 0.0627 -5.000 -0.6017 0.01062 0.00409 0.0090 1.0000 0.0732 -4.750 -0.5822 0.01027 0.00380 0.0105 1.0000 0.0882 -4.500 -0.5616 0.00992 0.00356 0.0117 0.9997 0.1102 -4.250 -0.5244 0.00946 0.00330 0.0093 0.9960 0.1514 -4.000 -0.4883 0.00896 0.00304 0.0072 0.9916 0.2031 -3.750 -0.4526 0.00845 0.00281 0.0052 0.9867 0.2662 -3.500 -0.4164 0.00791 0.00259 0.0030 0.9823 0.3444 -3.250 -0.3829 0.00742 0.00240 0.0016 0.9755 0.4211 -3.000 -0.3457 0.00702 0.00227 -0.0006 0.9712 0.4898 -2.750 -0.3125 0.00674 0.00216 -0.0017 0.9628 0.5417 -2.500 -0.2761 0.00651 0.00206 -0.0034 0.9561 0.5843 -2.250 -0.2446 0.00634 0.00199 -0.0040 0.9441 0.6177 -2.000 -0.2135 0.00621 0.00192 -0.0045 0.9311 0.6464 -1.750 -0.1841 0.00611 0.00186 -0.0045 0.9163 0.6706 -1.500 -0.1563 0.00605 0.00181 -0.0042 0.9002 0.6923 -1.250 -0.1296 0.00600 0.00177 -0.0036 0.8834 0.7117 -1.000 -0.1034 0.00597 0.00173 -0.0029 0.8666 0.7297 -0.750 -0.0774 0.00595 0.00171 -0.0022 0.8499 0.7471 -0.500 -0.0514 0.00594 0.00169 -0.0015 0.8333 0.7641 -0.250 -0.0257 0.00594 0.00168 -0.0008 0.8166 0.7817 0.000 0.0000 0.00594 0.00168 0.0000 0.7993 0.7993 0.250 0.0257 0.00594 0.00168 0.0008 0.7816 0.8165 0.500 0.0514 0.00594 0.00169 0.0015 0.7641 0.8333 0.750 0.0773 0.00595 0.00171 0.0023 0.7471 0.8500 1.000 0.1034 0.00597 0.00173 0.0030 0.7297 0.8666 1.250 0.1296 0.00600 0.00177 0.0036 0.7118 0.8834 1.500 0.1563 0.00605 0.00181 0.0042 0.6923 0.9002 1.750 0.1841 0.00611 0.00186 0.0045 0.6705 0.9164 2.000 0.2134 0.00621 0.00192 0.0045 0.6462 0.9311 2.250 0.2445 0.00635 0.00199 0.0040 0.6173 0.9441 2.500 0.2761 0.00651 0.00206 0.0035 0.5839 0.9561 2.750 0.3125 0.00674 0.00216 0.0017 0.5420 0.9628 3.000 0.3457 0.00702 0.00227 0.0006 0.4902 0.9712 3.250 0.3830 0.00741 0.00240 -0.0016 0.4214 0.9755 3.750 0.4526 0.00846 0.00280 -0.0052 0.2657 0.9867 4.000 0.4884 0.00896 0.00304 -0.0072 0.2028 0.9917 4.250 0.5244 0.00946 0.00329 -0.0093 0.1511 0.9960 4.500 0.5617 0.00992 0.00356 -0.0117 0.1103 0.9998 4.750 0.5820 0.01026 0.00380 -0.0104 0.0884 1.0000 5.000 0.6015 0.01062 0.00408 -0.0089 0.0733 1.0000 5.250 0.6216 0.01098 0.00440 -0.0075 0.0627 1.0000 5.500 0.6417 0.01139 0.00478 -0.0060 0.0545 1.0000 5.750 0.6624 0.01177 0.00514 -0.0047 0.0485 1.0000 6.000 0.6830 0.01221 0.00560 -0.0033 0.0440 1.0000 6.250 0.7044 0.01258 0.00596 -0.0021 0.0399 1.0000 6.500 0.7240 0.01320 0.00660 -0.0006 0.0364 1.0000 6.750 0.7459 0.01357 0.00701 0.0005 0.0338 1.0000 7.000 0.7667 0.01408 0.00751 0.0018 0.0312 1.0000 7.250 0.7862 0.01477 0.00825 0.0032 0.0290 1.0000 7.500 0.8077 0.01523 0.00877 0.0044 0.0273 1.0000 7.750 0.8287 0.01575 0.00930 0.0055 0.0256 1.0000 8.000 0.8444 0.01703 0.01061 0.0074 0.0239 1.0000 8.250 0.8659 0.01758 0.01125 0.0085 0.0231 1.0000 8.500 0.8867 0.01824 0.01199 0.0097 0.0220 1.0000 8.750 0.9072 0.01893 0.01274 0.0109 0.0210 1.0000 9.000 0.9274 0.01960 0.01344 0.0119 0.0201 1.0000 9.250 0.9434 0.02107 0.01497 0.0135 0.0191 1.0000 9.500 0.9615 0.02223 0.01628 0.0148 0.0186 1.0000 9.750 0.9800 0.02325 0.01745 0.0161 0.0181 1.0000 10.000 0.9972 0.02444 0.01879 0.0175 0.0176 1.0000 10.250 1.0135 0.02568 0.02019 0.0189 0.0171 1.0000 10.500 1.0284 0.02702 0.02167 0.0204 0.0167 1.0000 10.750 1.0416 0.02847 0.02330 0.0220 0.0164 1.0000 11.000 1.0538 0.02982 0.02477 0.0237 0.0160 1.0000 11.250 1.0631 0.03143 0.02654 0.0255 0.0158 1.0000 11.500 1.0707 0.03298 0.02820 0.0275 0.0155 1.0000 11.750 1.0707 0.03500 0.03038 0.0302 0.0153 1.0000 12.000 1.0635 0.03737 0.03293 0.0334 0.0152 1.0000 12.250 1.0535 0.03998 0.03575 0.0360 0.0152 1.0000 12.500 1.0303 0.04424 0.04027 0.0377 0.0150 1.0000 12.750 1.0218 0.04711 0.04331 0.0379 0.0151 1.0000 13.000 1.0015 0.05185 0.04827 0.0368 0.0150 1.0000 13.250 0.9808 0.05734 0.05396 0.0342 0.0150 1.0000 13.500 0.9548 0.06453 0.06136 0.0296 0.0150 1.0000 13.750 0.9431 0.07055 0.06759 0.0247 0.0154 1.0000 14.000 0.9100 0.08162 0.07886 0.0164 0.0154 1.0000