10x6E (10x6E.dat) v2025-1001 Simulation Date: 02/24/2026 ----- AIRFOIL SUMMARY DATA ----- DEFINITIONS: THE QUOTED PITCH REFLECTS, IN GENERAL, ANGULAR MEASURE AS DEFINED WITH A FLAT BOTTOM SURFACE. THIS WILL AGREE WITH A PRATHER GAGE MEASUREMENT OVER MOST OF THE EFFECTIVE PORTION OF THE BLADE. (NOTE: QUOTED=INPUT) THE LE-TE MEASURE IS DEFINED IN TERMS OF LEADING EDGE AND TRAILING EDGE (MOLD) PARTING LINE DATUMS. THE PRATHER MEASURE REFLECTS THE MOST LIKELY PITCH INTERPRETATION FROM A PITCH MEASUREMENT DEVICE THAT RESTS AGAINST THE LOWER SURFACE. SWEEP & RAKE ARE DEFINED WITH (MOLD) LE PARTING LINE. ZHIGH IS HIGHEST ELEVATION ON TOP SURFACE. TWIST IS DEFINED WITH (MOLD) LE AND TE PARTING LINE DATUMS. CHORD IS THE LENGTH BETWEEN (MOLD) LE AND TE PARTING LINES. CGY IS MASS OFFSET, FORE-AFT. CGZ IS MASS OFFSET, ELEVATION. STATION CHORD PITCH PITCH PITCH SWEEP(Y) RAKE(Z) THICKNESS TWIST MAX-THICK CROSS-SECTION ZHIGH CGY CGZ (IN) (IN) (QUOTED) (LE-TE) (PRATHER) (IN) (IN) RATIO (DEG) (IN) (IN**2) (IN) (IN) (IN) 0.0000 0.8000 6.0000 0.0000 0.0000 0.4000 0.0000 0.4169 0.0000 0.3335 0.0000 0.0700 0.0000 0.0000 0.1100 0.7637 6.0000 0.0142 -0.3920 0.3947 0.0115 0.3785 1.1748 0.2891 0.1931 0.0796 0.0094 -0.0643 0.2200 0.7250 6.0000 0.1113 -0.7661 0.3901 0.0426 0.3435 4.6044 0.2491 0.1943 0.1054 0.0254 -0.0496 0.3300 0.6917 6.0000 0.3689 -0.9845 0.3865 0.0877 0.3117 10.0894 0.2156 0.1876 0.1409 0.0435 -0.0263 0.4400 0.6718 6.0000 0.8525 -0.8675 0.3840 0.1418 0.2830 17.1378 0.1901 0.1716 0.1825 0.0621 0.0039 0.5500 0.6713 6.0000 1.5990 -0.2893 0.3831 0.2000 0.2571 24.8302 0.1726 0.1512 0.2282 0.0797 0.0380 0.6600 0.6913 6.0000 2.5909 0.7907 0.3839 0.2572 0.2340 31.9966 0.1618 0.1302 0.2754 0.0948 0.0732 0.7700 0.7281 6.0000 3.7294 2.2717 0.3866 0.3087 0.2135 37.6267 0.1554 0.1112 0.3201 0.1062 0.1069 0.8800 0.7751 6.0000 4.8283 3.8092 0.3914 0.3495 0.1954 41.1284 0.1514 0.0960 0.3569 0.1128 0.1359 0.9900 0.8262 6.0000 5.6526 4.9871 0.3987 0.3747 0.1795 42.2624 0.1483 0.0861 0.3803 0.1131 0.1566 1.1000 0.8776 6.0000 5.9970 5.5240 0.4085 0.3794 0.1658 40.9478 0.1455 0.0832 0.3849 0.1049 0.1631 1.2106 0.9229 6.0000 6.0000 5.5949 0.4194 0.3694 0.1540 38.2659 0.1421 0.0848 0.3763 0.0913 0.1590 1.3321 0.9586 6.0000 6.0000 5.6612 0.4292 0.3578 0.1431 35.6359 0.1372 0.0848 0.3664 0.0790 0.1559 1.4541 0.9875 6.0000 6.0000 5.7169 0.4369 0.3456 0.1341 33.2928 0.1324 0.0842 0.3559 0.0681 0.1530 1.5762 1.0097 6.0000 6.0000 5.7609 0.4426 0.3328 0.1269 31.2092 0.1282 0.0834 0.3451 0.0583 0.1497 1.6983 1.0257 6.0000 6.0000 5.7939 0.4463 0.3196 0.1213 29.3488 0.1244 0.0827 0.3340 0.0492 0.1459 1.8203 1.0358 6.0000 6.0000 5.8162 0.4481 0.3060 0.1170 27.6809 0.1212 0.0820 0.3225 0.0410 0.1415 1.9424 1.0402 6.0000 6.0000 5.8290 0.4481 0.2920 0.1139 26.1797 0.1185 0.0814 0.3108 0.0334 0.1364 2.0645 1.0394 6.0000 6.0000 5.8332 0.4464 0.2778 0.1117 24.8230 0.1161 0.0808 0.2988 0.0265 0.1306 2.1866 1.0338 6.0000 6.0000 5.8303 0.4431 0.2634 0.1102 23.5923 0.1139 0.0802 0.2865 0.0202 0.1244 2.3086 1.0235 6.0000 6.0000 5.8241 0.4382 0.2489 0.1090 22.4718 0.1116 0.0791 0.2740 0.0145 0.1178 2.4307 1.0090 6.0000 6.0000 5.8167 0.4318 0.2345 0.1079 21.4481 0.1089 0.0774 0.2613 0.0095 0.1111 2.5528 0.9906 6.0000 6.0000 5.8053 0.4240 0.2203 0.1069 20.5097 0.1059 0.0752 0.2485 0.0051 0.1043 2.6748 0.9686 6.0000 6.0000 5.7917 0.4150 0.2062 0.1059 19.6469 0.1026 0.0724 0.2356 0.0013 0.0975 2.7969 0.9435 6.0000 6.0000 5.7771 0.4046 0.1923 0.1050 18.8512 0.0991 0.0692 0.2225 -0.0018 0.0907 2.9190 0.9154 6.0000 6.0000 5.7609 0.3932 0.1787 0.1042 18.1153 0.0954 0.0656 0.2094 -0.0043 0.0840 3.0410 0.8849 6.0000 6.0000 5.7448 0.3806 0.1653 0.1035 17.4331 0.0915 0.0616 0.1962 -0.0062 0.0773 3.1631 0.8521 6.0000 6.0000 5.7295 0.3671 0.1521 0.1028 16.7989 0.0876 0.0574 0.1830 -0.0077 0.0706 3.2852 0.8175 6.0000 6.0000 5.7152 0.3526 0.1392 0.1021 16.2080 0.0835 0.0530 0.1698 -0.0088 0.0641 3.4072 0.7813 6.0000 6.0000 5.7026 0.3374 0.1266 0.1016 15.6563 0.0793 0.0485 0.1566 -0.0096 0.0576 3.5293 0.7440 6.0000 6.0000 5.6923 0.3214 0.1142 0.1010 15.1401 0.0752 0.0440 0.1435 -0.0102 0.0511 3.6514 0.7059 6.0000 6.0000 5.6845 0.3047 0.1021 0.1006 14.6561 0.0710 0.0395 0.1305 -0.0108 0.0447 3.7734 0.6672 6.0000 6.0000 5.6783 0.2875 0.0902 0.1002 14.2014 0.0669 0.0353 0.1176 -0.0115 0.0382 3.8955 0.6284 6.0000 6.0000 5.6726 0.2697 0.0786 0.0999 13.7736 0.0628 0.0313 0.1048 -0.0125 0.0316 4.0176 0.5898 6.0000 6.0000 5.6676 0.2516 0.0672 0.0997 13.3704 0.0588 0.0275 0.0922 -0.0139 0.0248 4.1397 0.5516 6.0000 6.0000 5.6631 0.2331 0.0560 0.0995 12.9897 0.0549 0.0241 0.0798 -0.0157 0.0179 4.2617 0.5144 6.0000 6.0000 5.6589 0.2144 0.0450 0.0994 12.6297 0.0511 0.0210 0.0676 -0.0182 0.0109 4.3838 0.4783 6.0000 6.0000 5.6448 0.1954 0.0343 0.0993 12.2889 0.0475 0.0181 0.0554 -0.0212 0.0034 4.5059 0.4438 6.0000 6.0000 5.6114 0.1765 0.0239 0.0993 11.9657 0.0441 0.0156 0.0431 -0.0250 -0.0045 4.6279 0.4112 6.0000 6.0000 5.5546 0.1575 0.0137 0.0994 11.6588 0.0409 0.0135 0.0308 -0.0296 -0.0128 4.7450 0.3820 6.0000 6.0000 5.4686 0.1393 0.0042 0.0995 11.3789 0.0380 0.0116 0.0192 -0.0347 -0.0211 4.7753 0.3727 6.0000 6.0000 5.3803 0.1326 0.0013 0.0996 11.3085 0.0371 0.0111 0.0157 -0.0373 -0.0235 4.8005 0.3621 6.0000 6.0000 5.3018 0.1240 -0.0016 0.0996 11.2506 0.0361 0.0105 0.0121 -0.0410 -0.0260 4.8258 0.3485 6.0000 6.0000 5.2241 0.1125 -0.0051 0.0997 11.1932 0.0347 0.0097 0.0079 -0.0465 -0.0288 4.8510 0.3315 6.0000 6.0000 5.1558 0.0975 -0.0093 0.0997 11.1364 0.0331 0.0088 0.0029 -0.0539 -0.0320 4.8763 0.3103 6.0000 6.0000 5.0936 0.0782 -0.0142 0.0998 11.0801 0.0310 0.0077 -0.0031 -0.0636 -0.0358 4.9015 0.2836 6.0000 6.0000 5.0443 0.0534 -0.0202 0.0998 11.0245 0.0283 0.0065 -0.0103 -0.0765 -0.0402 4.9268 0.2483 6.0000 6.0000 5.0256 0.0201 -0.0278 0.0999 10.9693 0.0248 0.0050 -0.0193 -0.0939 -0.0455 4.9520 0.1957 6.0000 6.0000 5.1065 -0.0303 -0.0386 0.0999 10.9147 0.0196 0.0031 -0.0321 -0.1208 -0.0529 4.9773 0.1036 6.0000 6.0000 5.7996 -0.1198 -0.0568 0.1000 10.8607 0.0104 0.0009 -0.0534 -0.1688 -0.0647 5.0000 0.0163 6.0000 6.0030 6.0030 -0.2046 -0.0738 0.1000 10.8178 0.0016 0.0000 -0.0738 0.0000 0.0000 RADIUS: 5.00 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.10 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.045474 TOTAL WEIGHT (Kg) = 0.020623 TOTAL VOLUME (IN**3) = 0.740826 TOTAL PROJECTED AREA (IN**2) = 7.0622 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000490 MOMENT OF INERTIA (Kg-M**2) = 0.000055 STATIC MOMENT, ONE SIDE (IN-LB) = 0.036835 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.700 DENSITY (INPUT FILE, LB/IN**3) = 0.6138E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6138E-01 ACTIVITY FACTOR = 91.861 INNER LIMIT (NORMALIZED BY RADIUS) = 0.080 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 14502.72 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.10, E63 (Transition Start, Airfoil 1) AIRFOIL2: 3.66, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412