XFOIL Version 6.96 Calculated polar for: NPL 9627 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 ------ -------- --------- --------- -------- -------- -------- -14.250 -0.7733 0.11156 0.10893 -0.0023 1.0000 0.0172 -14.000 -0.8005 0.10097 0.09829 -0.0081 1.0000 0.0170 -13.750 -0.8381 0.08810 0.08531 -0.0165 1.0000 0.0167 -13.500 -0.8751 0.07600 0.07303 -0.0254 1.0000 0.0164 -13.250 -0.9087 0.06544 0.06224 -0.0338 1.0000 0.0162 -13.000 -0.9399 0.05674 0.05327 -0.0402 1.0000 0.0160 -12.750 -0.9688 0.04989 0.04613 -0.0437 1.0000 0.0158 -12.500 -0.9915 0.04490 0.04085 -0.0444 1.0000 0.0157 -12.250 -1.0082 0.04111 0.03679 -0.0431 1.0000 0.0157 -12.000 -1.0192 0.03814 0.03357 -0.0406 1.0000 0.0157 -11.750 -1.0261 0.03556 0.03075 -0.0375 1.0000 0.0157 -11.500 -1.0263 0.03286 0.02776 -0.0350 1.0000 0.0157 -11.250 -1.0203 0.03055 0.02520 -0.0328 1.0000 0.0157 -11.000 -1.0100 0.02866 0.02311 -0.0310 1.0000 0.0157 -10.750 -0.9969 0.02705 0.02133 -0.0293 1.0000 0.0158 -10.500 -0.9822 0.02562 0.01975 -0.0278 1.0000 0.0160 -10.250 -0.9663 0.02432 0.01833 -0.0263 1.0000 0.0162 -10.000 -0.9496 0.02314 0.01702 -0.0247 1.0000 0.0164 -9.750 -0.9325 0.02204 0.01580 -0.0232 1.0000 0.0167 -9.500 -0.9150 0.02105 0.01469 -0.0216 1.0000 0.0171 -9.250 -0.8984 0.02005 0.01361 -0.0199 1.0000 0.0175 -9.000 -0.8805 0.01933 0.01290 -0.0183 1.0000 0.0179 -8.750 -0.8615 0.01878 0.01232 -0.0168 1.0000 0.0185 -8.500 -0.8427 0.01820 0.01168 -0.0153 1.0000 0.0195 -8.250 -0.8244 0.01757 0.01095 -0.0135 1.0000 0.0205 -8.000 -0.8063 0.01701 0.01042 -0.0119 1.0000 0.0214 -7.750 -0.7870 0.01659 0.00996 -0.0103 1.0000 0.0226 -7.500 -0.7674 0.01622 0.00950 -0.0087 1.0000 0.0237 -7.250 -0.7505 0.01557 0.00888 -0.0069 1.0000 0.0246 -7.000 -0.7316 0.01517 0.00846 -0.0053 1.0000 0.0257 -6.750 -0.7122 0.01482 0.00805 -0.0037 1.0000 0.0269 -6.500 -0.6943 0.01428 0.00752 -0.0020 1.0000 0.0282 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0.5244 -1.500 -0.0754 0.00684 0.00201 -0.0151 0.8253 0.5819 -1.250 -0.0514 0.00661 0.00196 -0.0141 0.8041 0.6490 -1.000 -0.0274 0.00644 0.00193 -0.0129 0.7814 0.7092 -0.750 -0.0028 0.00636 0.00192 -0.0119 0.7586 0.7586 -0.500 0.0225 0.00632 0.00194 -0.0109 0.7373 0.7977 0.000 0.0738 0.00639 0.00200 -0.0092 0.6934 0.8569 0.250 0.0996 0.00648 0.00203 -0.0084 0.6715 0.8803 0.500 0.1257 0.00658 0.00208 -0.0076 0.6519 0.9002 0.750 0.1524 0.00669 0.00215 -0.0070 0.6342 0.9172 1.000 0.1802 0.00683 0.00222 -0.0066 0.6159 0.9315 1.250 0.2095 0.00697 0.00230 -0.0065 0.5959 0.9431 1.500 0.2390 0.00712 0.00238 -0.0066 0.5762 0.9538 1.750 0.2716 0.00729 0.00246 -0.0074 0.5558 0.9619 2.000 0.3052 0.00745 0.00255 -0.0085 0.5358 0.9687 2.250 0.3427 0.00764 0.00263 -0.0104 0.5133 0.9731 2.500 0.3780 0.00782 0.00272 -0.0120 0.4922 0.9786 2.750 0.4163 0.00798 0.00280 -0.0142 0.4674 0.9821 3.000 0.4549 0.00819 0.00288 -0.0165 0.4377 0.9854 3.250 0.4919 0.00839 0.00298 -0.0185 0.4098 0.9895 3.500 0.5283 0.00862 0.00308 -0.0205 0.3798 0.9933 3.750 0.5675 0.00889 0.00320 -0.0231 0.3416 0.9962 4.000 0.6061 0.00924 0.00335 -0.0256 0.3013 0.9995 4.250 0.6314 0.00954 0.00349 -0.0254 0.2657 1.0000 4.500 0.6532 0.00991 0.00367 -0.0244 0.2243 1.0000 4.750 0.6729 0.01052 0.00395 -0.0232 0.1608 1.0000 5.000 0.6923 0.01112 0.00428 -0.0219 0.1179 1.0000 5.250 0.7131 0.01150 0.00456 -0.0207 0.1045 1.0000 5.500 0.7345 0.01180 0.00483 -0.0195 0.0980 1.0000 5.750 0.7557 0.01211 0.00511 -0.0182 0.0935 1.0000 6.000 0.7764 0.01247 0.00545 -0.0169 0.0898 1.0000 6.250 0.7981 0.01273 0.00574 -0.0158 0.0877 1.0000 6.500 0.8195 0.01303 0.00605 -0.0146 0.0854 1.0000 6.750 0.8404 0.01339 0.00641 -0.0133 0.0829 1.0000 7.000 0.8595 0.01393 0.00693 -0.0118 0.0801 1.0000 7.250 0.8816 0.01421 0.00725 -0.0107 0.0784 1.0000 7.500 0.9032 0.01453 0.00760 -0.0096 0.0764 1.0000 7.750 0.9245 0.01490 0.00800 -0.0084 0.0742 1.0000 8.000 0.9440 0.01546 0.00854 -0.0071 0.0718 1.0000 8.250 0.9643 0.01599 0.00910 -0.0059 0.0696 1.0000 8.500 0.9870 0.01631 0.00947 -0.0050 0.0673 1.0000 8.750 1.0089 0.01671 0.00988 -0.0041 0.0649 1.0000 9.000 1.0257 0.01761 0.01075 -0.0026 0.0621 1.0000 9.250 1.0496 0.01783 0.01106 -0.0020 0.0600 1.0000 9.500 1.0719 0.01819 0.01145 -0.0012 0.0575 1.0000 9.750 1.0917 0.01876 0.01201 -0.0001 0.0555 1.0000 10.000 1.1113 0.01938 0.01268 0.0010 0.0535 1.0000 10.250 1.1331 0.01976 0.01312 0.0018 0.0516 1.0000 10.500 1.1543 0.02016 0.01354 0.0027 0.0498 1.0000 10.750 1.1713 0.02090 0.01426 0.0040 0.0483 1.0000 11.000 1.1904 0.02146 0.01491 0.0051 0.0471 1.0000 11.250 1.2090 0.02202 0.01555 0.0063 0.0458 1.0000 11.500 1.2264 0.02258 0.01616 0.0076 0.0447 1.0000 11.750 1.2416 0.02316 0.01678 0.0092 0.0437 1.0000 12.000 1.2535 0.02399 0.01762 0.0112 0.0428 1.0000 12.250 1.2649 0.02494 0.01863 0.0130 0.0420 1.0000 12.500 1.2784 0.02573 0.01954 0.0145 0.0412 1.0000 12.750 1.2915 0.02657 0.02046 0.0159 0.0402 1.0000 13.000 1.3043 0.02744 0.02138 0.0171 0.0393 1.0000 13.250 1.3163 0.02839 0.02238 0.0182 0.0385 1.0000 13.500 1.3239 0.02978 0.02378 0.0194 0.0376 1.0000 13.750 1.3326 0.03117 0.02528 0.0204 0.0369 1.0000 14.000 1.3418 0.03258 0.02681 0.0212 0.0361 1.0000 14.250 1.3501 0.03412 0.02846 0.0217 0.0354 1.0000 14.500 1.3576 0.03581 0.03023 0.0221 0.0347 1.0000 14.750 1.3640 0.03768 0.03217 0.0223 0.0341 1.0000 15.000 1.3681 0.03987 0.03441 0.0223 0.0335 1.0000 15.250 1.3678 0.04254 0.03711 0.0225 0.0329 1.0000 15.500 1.3697 0.04516 0.03987 0.0221 0.0325 1.0000 15.750 1.3709 0.04797 0.04284 0.0216 0.0320 1.0000 16.000 1.3707 0.05098 0.04598 0.0208 0.0315 1.0000 16.250 1.3694 0.05421 0.04933 0.0199 0.0310 1.0000 16.500 1.3672 0.05761 0.05284 0.0188 0.0306 1.0000 16.750 1.3639 0.06120 0.05652 0.0176 0.0301 1.0000 17.000 1.3599 0.06494 0.06035 0.0162 0.0298 1.0000 17.250 1.3549 0.06890 0.06437 0.0147 0.0294 1.0000 17.500 1.3486 0.07294 0.06846 0.0134 0.0290 1.0000 17.750 1.3395 0.07749 0.07311 0.0118 0.0286 1.0000 18.000 1.3286 0.08283 0.07862 0.0092 0.0284 1.0000 18.250 1.3164 0.08844 0.08439 0.0064 0.0281 1.0000 18.500 1.3027 0.09446 0.09057 0.0033 0.0279 1.0000 18.750 1.2880 0.10079 0.09705 0.0000 0.0276 1.0000 19.000 1.2719 0.10747 0.10388 -0.0035 0.0274 1.0000 19.250 1.2548 0.11451 0.11107 -0.0074 0.0271 1.0000