NACA 66,2-(1.8)15.5 A=.6 P-51 ROOT AIRFOIL 1.000000 0.000000 0.990015 0.000806 0.985028 0.001395 0.975063 0.002806 0.950185 0.007258 0.925343 0.012562 0.900523 0.018381 0.875716 0.024511 0.850910 0.030813 0.826100 0.037195 0.801278 0.043586 0.776437 0.049884 0.751567 0.055981 0.726662 0.061803 0.701715 0.067315 0.676719 0.072485 0.651662 0.077171 0.626521 0.081158 0.601224 0.084284 0.575888 0.086589 0.550637 0.088275 0.525411 0.089490 0.500199 0.090291 0.474997 0.090707 0.449804 0.090757 0.424618 0.090457 0.399439 0.089799 0.374267 0.088803 0.349102 0.087456 0.323944 0.085764 0.298795 0.083712 0.273655 0.081290 0.248524 0.078473 0.223406 0.075244 0.198300 0.071568 0.173210 0.067405 0.148140 0.062683 0.123094 0.057294 0.098080 0.051140 0.073107 0.044072 0.048200 0.035673 0.023406 0.025158 0.018467 0.022686 0.011904 0.018371 0.008658 0.016615 0.006244 0.014564 0.003870 0.012035 0.001682 0.008603 0.000000 0.000000 0.003318 -0.007958 0.006130 -0.010868 0.008756 -0.012924 0.011342 -0.014531 0.013906 -0.015867 0.021533 -0.019020 0.026594 -0.020778 0.051800 -0.028184 0.076893 -0.033973 0.101920 -0.038767 0.126906 -0.042950 0.151860 -0.046494 0.176790 -0.049600 0.201700 -0.052313 0.226594 -0.054690 0.251476 -0.056761 0.276345 -0.058552 0.301205 -0.060074 0.326056 -0.061348 0.350898 -0.062382 0.375733 -0.063188 0.400561 -0.063760 0.425382 -0.064111 0.450196 -0.064225 0.475003 -0.064110 0.499801 -0.063757 0.524589 -0.063154 0.549363 -0.062284 0.574112 -0.061180 0.598776 -0.059516 0.623479 -0.057380 0.648338 -0.054575 0.673281 -0.051217 0.698285 -0.047492 0.723338 -0.043517 0.748433 -0.039370 0.773563 -0.034881 0.798722 -0.030297 0.823900 -0.025648 0.849090 -0.021021 0.874284 -0.016472 0.899477 -0.012076 0.924657 -0.007953 0.949815 -0.004289 0.974937 -0.001389 0.984972 -0.000565 0.989985 -0.000261 1.000000 0.000000