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 = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.5392 0.08990 0.08433 -0.0285 1.0000 0.0311 -9.750 -0.5412 0.08497 0.07944 -0.0310 1.0000 0.0309 -9.500 -0.5474 0.07872 0.07322 -0.0350 1.0000 0.0305 -9.250 -0.5604 0.07194 0.06644 -0.0401 1.0000 0.0300 -9.000 -0.5817 0.06584 0.06030 -0.0442 1.0000 0.0296 -8.750 -0.6014 0.06107 0.05542 -0.0462 1.0000 0.0293 -8.500 -0.6141 0.05632 0.05047 -0.0472 1.0000 0.0290 -8.250 -0.6210 0.05182 0.04571 -0.0474 1.0000 0.0288 -8.000 -0.6222 0.04770 0.04127 -0.0470 1.0000 0.0287 -7.750 -0.6188 0.04391 0.03713 -0.0462 1.0000 0.0289 -7.500 -0.6108 0.04069 0.03356 -0.0453 1.0000 0.0295 -7.250 -0.6007 0.03742 0.02980 -0.0443 1.0000 0.0305 -7.000 -0.5876 0.03453 0.02644 -0.0431 1.0000 0.0315 -6.750 -0.5704 0.03286 0.02464 -0.0422 1.0000 0.0323 -6.500 -0.5529 0.03086 0.02238 -0.0410 1.0000 0.0329 -6.250 -0.5343 0.02894 0.02018 -0.0398 1.0000 0.0337 -6.000 -0.5149 0.02715 0.01806 -0.0386 1.0000 0.0350 -5.750 -0.4951 0.02581 0.01655 -0.0374 1.0000 0.0367 -5.500 -0.4751 0.02476 0.01546 -0.0363 1.0000 0.0384 -5.250 -0.4546 0.02354 0.01408 -0.0351 1.0000 0.0399 -5.000 -0.4340 0.02243 0.01284 -0.0338 1.0000 0.0414 -4.750 -0.4141 0.02164 0.01210 -0.0327 1.0000 0.0436 -4.500 -0.3936 0.02085 0.01124 -0.0315 1.0000 0.0462 -4.250 -0.3735 0.02003 0.01044 -0.0303 1.0000 0.0481 -4.000 -0.3446 0.01934 0.00977 -0.0309 0.9969 0.0518 -3.750 -0.3104 0.01859 0.00903 -0.0325 0.9915 0.0558 -3.500 -0.2753 0.01794 0.00837 -0.0343 0.9860 0.0607 -3.250 -0.2414 0.01734 0.00777 -0.0359 0.9799 0.0692 -3.000 -0.2054 0.01670 0.00720 -0.0378 0.9746 0.0841 -2.750 -0.1732 0.01579 0.00666 -0.0393 0.9676 0.1426 -2.500 -0.1435 0.01403 0.00652 -0.0410 0.9626 0.4776 -2.250 -0.1146 0.01415 0.00695 -0.0407 0.9543 0.5977 -2.000 -0.0813 0.01455 0.00747 -0.0407 0.9487 0.6624 -1.750 -0.0556 0.01484 0.00783 -0.0392 0.9397 0.7011 -1.500 -0.0203 0.01490 0.00785 -0.0401 0.9345 0.7197 -1.250 0.0108 0.01483 0.00768 -0.0408 0.9255 0.7279 -1.000 0.0466 0.01474 0.00755 -0.0421 0.9194 0.7340 -0.750 0.0777 0.01467 0.00743 -0.0426 0.9100 0.7412 -0.500 0.1135 0.01457 0.00729 -0.0439 0.9031 0.7477 -0.250 0.1437 0.01451 0.00722 -0.0442 0.8936 0.7540 0.000 0.1786 0.01443 0.00710 -0.0454 0.8860 0.7610 0.250 0.2077 0.01436 0.00706 -0.0453 0.8758 0.7669 0.500 0.2417 0.01425 0.00695 -0.0461 0.8669 0.7733 0.750 0.2712 0.01414 0.00685 -0.0460 0.8522 0.7801 1.000 0.3016 0.01390 0.00661 -0.0455 0.8322 0.7859 1.250 0.3296 0.01365 0.00631 -0.0444 0.8013 0.7927 1.500 0.3571 0.01345 0.00602 -0.0432 0.7656 0.7992 1.750 0.3838 0.01335 0.00586 -0.0421 0.7337 0.8062 2.000 0.4109 0.01333 0.00579 -0.0414 0.7046 0.8139 2.250 0.4362 0.01333 0.00576 -0.0403 0.6697 0.8212 2.500 0.4615 0.01339 0.00573 -0.0392 0.6239 0.8304 2.750 0.4846 0.01353 0.00566 -0.0376 0.5538 0.8390 3.000 0.5047 0.01404 0.00564 -0.0357 0.4405 0.8495 3.250 0.5217 0.01498 0.00590 -0.0338 0.3036 0.8621 3.500 0.5410 0.01586 0.00629 -0.0325 0.2151 0.8778 4.000 0.5933 0.01699 0.00714 -0.0323 0.1565 0.9328 4.250 0.6230 0.01758 0.00765 -0.0331 0.1431 1.0000 4.500 0.6486 0.01820 0.00819 -0.0330 0.1331 1.0000 4.750 0.6740 0.01882 0.00876 -0.0329 0.1251 1.0000 5.000 0.6987 0.01949 0.00937 -0.0326 0.1180 1.0000 5.250 0.7237 0.02018 0.01005 -0.0323 0.1118 1.0000 5.500 0.7485 0.02088 0.01069 -0.0320 0.1056 1.0000 5.750 0.7730 0.02168 0.01147 -0.0316 0.1002 1.0000 6.000 0.7978 0.02239 0.01219 -0.0313 0.0942 1.0000 6.250 0.8218 0.02326 0.01298 -0.0309 0.0893 1.0000 6.500 0.8466 0.02402 0.01384 -0.0306 0.0839 1.0000 6.750 0.8703 0.02487 0.01462 -0.0302 0.0797 1.0000 7.000 0.8948 0.02578 0.01569 -0.0297 0.0751 1.0000 7.250 0.9183 0.02662 0.01653 -0.0293 0.0713 1.0000 7.500 0.9418 0.02767 0.01767 -0.0288 0.0679 1.0000 7.750 0.9650 0.02872 0.01885 -0.0283 0.0644 1.0000 8.000 0.9873 0.02959 0.01969 -0.0278 0.0620 1.0000 8.250 1.0095 0.03100 0.02136 -0.0271 0.0590 1.0000 8.500 1.0311 0.03233 0.02283 -0.0264 0.0568 1.0000 8.750 1.0521 0.03347 0.02402 -0.0258 0.0552 1.0000 9.000 1.0718 0.03511 0.02585 -0.0250 0.0535 1.0000 9.250 1.0890 0.03709 0.02817 -0.0240 0.0515 1.0000 9.500 1.1061 0.03862 0.02988 -0.0230 0.0499 1.0000 9.750 1.1233 0.03997 0.03133 -0.0221 0.0487 1.0000 10.000 1.1391 0.04168 0.03313 -0.0212 0.0479 1.0000 10.250 1.1438 0.04507 0.03707 -0.0193 0.0470 1.0000 10.500 1.1448 0.04848 0.04092 -0.0174 0.0462 1.0000 10.750 1.1412 0.05193 0.04475 -0.0153 0.0456 1.0000 11.000 1.1319 0.05533 0.04847 -0.0130 0.0451 1.0000 11.250 1.1166 0.05877 0.05219 -0.0106 0.0447 1.0000 11.500 1.0952 0.06294 0.05662 -0.0092 0.0445 1.0000 11.750 1.0651 0.06858 0.06254 -0.0097 0.0445 1.0000 12.000 1.0142 0.07841 0.07268 -0.0146 0.0449 1.0000