XFOIL Version 6.96 Calculated polar for: RAE(NPL) 5213 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 ------ -------- --------- --------- -------- -------- -------- -13.000 -0.5560 0.13461 0.13271 -0.0058 1.0000 0.0141 -12.750 -0.5538 0.13014 0.12824 -0.0076 1.0000 0.0141 -12.500 -0.7841 0.06579 0.06376 -0.0387 1.0000 0.0096 -12.250 -0.7743 0.06312 0.06110 -0.0409 1.0000 0.0097 -12.000 -0.7707 0.05929 0.05724 -0.0443 1.0000 0.0098 -11.750 -0.7720 0.05513 0.05303 -0.0480 1.0000 0.0099 -11.500 -0.7644 0.05313 0.05102 -0.0497 1.0000 0.0099 -11.250 -0.9348 0.02977 0.02624 -0.0558 1.0000 0.0093 -11.000 -0.9306 0.02732 0.02355 -0.0545 1.0000 0.0093 -10.750 -0.9320 0.02363 0.01945 -0.0526 1.0000 0.0094 -10.500 -0.9201 0.02174 0.01734 -0.0513 1.0000 0.0095 -10.250 -0.9045 0.02039 0.01585 -0.0501 1.0000 0.0097 -10.000 -0.8863 0.01947 0.01484 -0.0489 1.0000 0.0098 -9.750 -0.8669 0.01877 0.01409 -0.0479 1.0000 0.0100 -9.500 -0.8471 0.01814 0.01339 -0.0468 1.0000 0.0102 -9.250 -0.8274 0.01748 0.01267 -0.0456 1.0000 0.0104 -9.000 -0.8077 0.01684 0.01195 -0.0444 1.0000 0.0108 -8.750 -0.7883 0.01615 0.01117 -0.0431 1.0000 0.0110 -8.500 -0.7687 0.01552 0.01046 -0.0418 1.0000 0.0113 -8.250 -0.7455 0.01487 0.00972 -0.0412 0.9997 0.0117 -8.000 -0.7129 0.01416 0.00899 -0.0427 0.9982 0.0122 -7.750 -0.6790 0.01388 0.00871 -0.0441 0.9967 0.0128 -7.500 -0.6451 0.01344 0.00821 -0.0456 0.9952 0.0134 -7.250 -0.6114 0.01307 0.00778 -0.0469 0.9935 0.0140 -7.000 -0.5797 0.01238 0.00706 -0.0480 0.9912 0.0147 -6.750 -0.5460 0.01208 0.00677 -0.0494 0.9891 0.0154 -6.500 -0.5116 0.01173 0.00639 -0.0509 0.9874 0.0162 -6.250 -0.4765 0.01150 0.00611 -0.0524 0.9860 0.0170 -6.000 -0.4418 0.01085 0.00549 -0.0541 0.9848 0.0180 -5.750 -0.4104 0.01053 0.00516 -0.0549 0.9811 0.0190 -5.500 -0.3765 0.01026 0.00487 -0.0562 0.9784 0.0199 -5.250 -0.3431 0.00972 0.00432 -0.0575 0.9757 0.0211 -5.000 -0.3120 0.00945 0.00406 -0.0582 0.9709 0.0223 -4.750 -0.2817 0.00923 0.00382 -0.0586 0.9648 0.0233 -4.500 -0.2529 0.00881 0.00340 -0.0588 0.9579 0.0250 -4.250 -0.2235 0.00856 0.00315 -0.0590 0.9506 0.0263 -4.000 -0.1958 0.00831 0.00288 -0.0588 0.9416 0.0277 -3.750 -0.1678 0.00807 0.00263 -0.0587 0.9330 0.0295 -3.500 -0.1407 0.00789 0.00243 -0.0583 0.9216 0.0308 -3.250 -0.1136 0.00769 0.00220 -0.0580 0.9099 0.0328 -3.000 -0.0863 0.00755 0.00203 -0.0576 0.8981 0.0357 -2.750 -0.0592 0.00737 0.00185 -0.0573 0.8859 0.0425 -2.500 -0.0324 0.00705 0.00166 -0.0570 0.8726 0.0787 -2.250 -0.0064 0.00650 0.00145 -0.0568 0.8582 0.1863 -2.000 0.0187 0.00567 0.00120 -0.0567 0.8446 0.3701 -1.750 0.0449 0.00521 0.00110 -0.0564 0.8317 0.4929 -1.500 0.0723 0.00511 0.00109 -0.0562 0.8178 0.5408 -1.250 0.0998 0.00512 0.00108 -0.0558 0.8005 0.5661 -1.000 0.1267 0.00516 0.00107 -0.0553 0.7776 0.5864 -0.750 0.1540 0.00523 0.00109 -0.0549 0.7558 0.6046 -0.500 0.1815 0.00531 0.00112 -0.0546 0.7364 0.6211 -0.250 0.2090 0.00540 0.00118 -0.0542 0.7173 0.6355 0.000 0.2366 0.00547 0.00121 -0.0539 0.6992 0.6457 0.250 0.2644 0.00555 0.00123 -0.0537 0.6808 0.6506 0.500 0.2921 0.00565 0.00124 -0.0534 0.6561 0.6544 0.750 0.3194 0.00577 0.00125 -0.0531 0.6255 0.6581 1.000 0.3456 0.00596 0.00128 -0.0526 0.5775 0.6622 1.250 0.3709 0.00631 0.00136 -0.0521 0.5029 0.6661 1.500 0.3952 0.00683 0.00150 -0.0514 0.4080 0.6700 1.750 0.4190 0.00749 0.00170 -0.0508 0.2967 0.6736 2.000 0.4432 0.00806 0.00189 -0.0502 0.2033 0.6776 2.250 0.4685 0.00849 0.00208 -0.0498 0.1450 0.6817 2.500 0.4953 0.00874 0.00223 -0.0495 0.1219 0.6857 2.750 0.5226 0.00893 0.00236 -0.0493 0.1107 0.6896 3.000 0.5497 0.00913 0.00251 -0.0490 0.1025 0.6933 3.250 0.5771 0.00925 0.00265 -0.0488 0.0980 0.6976 3.500 0.6039 0.00946 0.00282 -0.0486 0.0909 0.7018 3.750 0.6315 0.00958 0.00295 -0.0484 0.0876 0.7061 4.000 0.6587 0.00975 0.00310 -0.0482 0.0835 0.7101 4.250 0.6853 0.00995 0.00330 -0.0479 0.0790 0.7148 4.500 0.7127 0.01005 0.00343 -0.0477 0.0763 0.7195 4.750 0.7396 0.01023 0.00359 -0.0475 0.0724 0.7246 5.000 0.7664 0.01042 0.00378 -0.0472 0.0687 0.7298 5.250 0.7933 0.01055 0.00393 -0.0469 0.0653 0.7354 5.500 0.8196 0.01079 0.00415 -0.0466 0.0614 0.7414 5.750 0.8465 0.01093 0.00432 -0.0464 0.0585 0.7476 6.000 0.8725 0.01117 0.00455 -0.0460 0.0548 0.7552 6.250 0.8990 0.01135 0.00476 -0.0457 0.0518 0.7634 6.500 0.9245 0.01161 0.00503 -0.0453 0.0480 0.7733 6.750 0.9505 0.01180 0.00526 -0.0449 0.0449 0.7845 7.000 0.9755 0.01207 0.00557 -0.0444 0.0414 0.7994 7.250 1.0003 0.01231 0.00587 -0.0438 0.0384 0.8216 7.500 1.0228 0.01247 0.00621 -0.0427 0.0361 0.8729 7.750 1.0497 0.01262 0.00652 -0.0425 0.0340 1.0000 8.000 1.0744 0.01306 0.00695 -0.0420 0.0323 1.0000 8.250 1.0995 0.01340 0.00731 -0.0416 0.0311 1.0000 8.500 1.1242 0.01379 0.00770 -0.0411 0.0300 1.0000 8.750 1.1476 0.01431 0.00823 -0.0404 0.0289 1.0000 9.000 1.1715 0.01477 0.00872 -0.0398 0.0282 1.0000 9.250 1.1956 0.01517 0.00916 -0.0392 0.0276 1.0000 9.500 1.2194 0.01560 0.00961 -0.0386 0.0269 1.0000 9.750 1.2425 0.01607 0.01011 -0.0379 0.0263 1.0000 10.000 1.2649 0.01661 0.01068 -0.0371 0.0258 1.0000 10.250 1.2853 0.01735 0.01145 -0.0361 0.0252 1.0000 10.500 1.3053 0.01811 0.01226 -0.0350 0.0248 1.0000 10.750 1.3271 0.01863 0.01284 -0.0342 0.0246 1.0000 11.000 1.3481 0.01921 0.01348 -0.0332 0.0243 1.0000 11.250 1.3684 0.01983 0.01417 -0.0322 0.0240 1.0000 11.500 1.3879 0.02049 0.01488 -0.0311 0.0237 1.0000 11.750 1.4067 0.02118 0.01563 -0.0299 0.0234 1.0000 12.000 1.4246 0.02189 0.01640 -0.0286 0.0231 1.0000 12.250 1.4414 0.02265 0.01722 -0.0272 0.0229 1.0000 12.500 1.4569 0.02344 0.01807 -0.0257 0.0227 1.0000 12.750 1.4693 0.02427 0.01895 -0.0236 0.0224 1.0000 13.000 1.4783 0.02519 0.01993 -0.0211 0.0222 1.0000 13.250 1.4854 0.02624 0.02106 -0.0186 0.0221 1.0000 13.500 1.4890 0.02761 0.02251 -0.0158 0.0219 1.0000 13.750 1.4900 0.02928 0.02428 -0.0132 0.0217 1.0000 14.000 1.4916 0.03099 0.02611 -0.0109 0.0215 1.0000 14.250 1.4968 0.03241 0.02763 -0.0091 0.0215 1.0000 14.500 1.5018 0.03388 0.02922 -0.0076 0.0214 1.0000 14.750 1.5051 0.03561 0.03105 -0.0062 0.0213 1.0000 15.000 1.5061 0.03765 0.03322 -0.0051 0.0212 1.0000 15.250 1.5066 0.03985 0.03553 -0.0042 0.0211 1.0000 15.500 1.5060 0.04230 0.03810 -0.0037 0.0210 1.0000 15.750 1.5031 0.04514 0.04106 -0.0035 0.0210 1.0000 16.000 1.4985 0.04836 0.04442 -0.0037 0.0209 1.0000 16.250 1.4926 0.05192 0.04812 -0.0044 0.0208 1.0000 16.500 1.4849 0.05596 0.05228 -0.0056 0.0207 1.0000 16.750 1.4758 0.06045 0.05692 -0.0073 0.0206 1.0000 17.000 1.4631 0.06579 0.06240 -0.0098 0.0206 1.0000 17.250 1.4491 0.07177 0.06853 -0.0130 0.0205 1.0000 17.500 1.4314 0.07880 0.07572 -0.0171 0.0205 1.0000 17.750 1.4107 0.08689 0.08397 -0.0221 0.0204 1.0000