14x8.5E (14x85E.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 -0.5880 0.0000 0.0000 0.4000 0.0000 0.4875 0.0000 0.3900 0.0000 0.1750 0.0000 0.0000 0.1820 0.7520 1.3619 0.0289 -0.6290 0.3942 0.0127 0.4776 1.4456 0.3592 0.2499 0.1829 0.0176 -0.0144 0.3640 0.7197 3.0767 0.2242 -1.1524 0.3945 0.0466 0.4478 5.5996 0.3223 0.2412 0.2028 0.0360 -0.0029 0.5460 0.7081 4.5562 0.7192 -1.2700 0.3997 0.0959 0.3988 11.8396 0.2824 0.2267 0.2304 0.0542 0.0161 0.7280 0.7215 5.8006 1.5816 -0.7774 0.4088 0.1552 0.3487 19.0738 0.2515 0.2092 0.2634 0.0711 0.0408 0.9100 0.7596 6.8098 2.7923 0.3840 0.4208 0.2189 0.3049 26.0294 0.2316 0.1904 0.2997 0.0860 0.0692 1.0920 0.8169 7.5839 4.2425 2.1065 0.4347 0.2816 0.2672 31.7298 0.2182 0.1713 0.3369 0.0982 0.0994 1.2740 0.8846 8.1227 5.7527 4.1178 0.4494 0.3377 0.2349 35.7034 0.2078 0.1530 0.3720 0.1073 0.1293 1.4560 0.9533 8.4264 7.1064 5.9198 0.4639 0.3819 0.2078 37.8400 0.1981 0.1364 0.4015 0.1125 0.1564 1.6380 1.0150 8.5000 8.0851 7.2518 0.4772 0.4086 0.1853 38.1527 0.1880 0.1231 0.4206 0.1126 0.1770 1.8200 1.0638 8.5000 8.4963 7.8958 0.4882 0.4124 0.1669 36.6118 0.1775 0.1156 0.4226 0.1044 0.1853 2.0009 1.1000 8.5000 8.5000 8.0229 0.4961 0.4001 0.1523 34.0632 0.1675 0.1130 0.4119 0.0891 0.1832 2.1623 1.1251 8.5000 8.5000 8.1040 0.5007 0.3886 0.1420 32.0319 0.1598 0.1114 0.4021 0.0755 0.1806 2.3226 1.1438 8.5000 8.5000 8.1631 0.5030 0.3769 0.1340 30.2195 0.1532 0.1099 0.3922 0.0629 0.1781 2.4828 1.1565 8.5000 8.5000 8.2052 0.5031 0.3648 0.1279 28.5846 0.1479 0.1087 0.3822 0.0510 0.1752 2.6431 1.1636 8.5000 8.5000 8.2326 0.5013 0.3525 0.1234 27.1047 0.1435 0.1077 0.3720 0.0396 0.1719 2.8034 1.1654 8.5000 8.5000 8.2478 0.4974 0.3399 0.1201 25.7604 0.1400 0.1068 0.3617 0.0288 0.1682 2.9637 1.1622 8.5000 8.5000 8.2536 0.4918 0.3271 0.1178 24.5352 0.1369 0.1058 0.3512 0.0186 0.1641 3.1239 1.1544 8.5000 8.5000 8.2564 0.4844 0.3143 0.1159 23.4150 0.1338 0.1045 0.3406 0.0088 0.1598 3.2842 1.1421 8.5000 8.5000 8.2588 0.4754 0.3017 0.1141 22.3875 0.1304 0.1025 0.3300 -0.0006 0.1553 3.4445 1.1258 8.5000 8.5000 8.2601 0.4648 0.2892 0.1124 21.4424 0.1266 0.0999 0.3192 -0.0095 0.1507 3.6048 1.1057 8.5000 8.5000 8.2584 0.4528 0.2769 0.1108 20.5704 0.1225 0.0968 0.3084 -0.0179 0.1461 3.7650 1.0822 8.5000 8.5000 8.2491 0.4395 0.2648 0.1093 19.7639 0.1183 0.0931 0.2975 -0.0257 0.1415 3.9253 1.0556 8.5000 8.5000 8.2352 0.4249 0.2529 0.1079 19.0160 0.1139 0.0890 0.2865 -0.0329 0.1370 4.0856 1.0261 8.5000 8.5000 8.2182 0.4091 0.2413 0.1066 18.3207 0.1094 0.0844 0.2754 -0.0395 0.1325 4.2459 0.9942 8.5000 8.5000 8.2012 0.3923 0.2298 0.1054 17.6729 0.1048 0.0796 0.2643 -0.0455 0.1281 4.4061 0.9601 8.5000 8.5000 8.1846 0.3746 0.2187 0.1043 17.0681 0.1001 0.0744 0.2531 -0.0510 0.1238 4.5664 0.9241 8.5000 8.5000 8.1701 0.3560 0.2077 0.1033 16.5021 0.0954 0.0690 0.2419 -0.0561 0.1196 4.7267 0.8865 8.5000 8.5000 8.1577 0.3366 0.1970 0.1024 15.9716 0.0907 0.0636 0.2307 -0.0607 0.1154 4.8870 0.8477 8.5000 8.5000 8.1489 0.3166 0.1865 0.1015 15.4732 0.0861 0.0581 0.2194 -0.0650 0.1112 5.0472 0.8080 8.5000 8.5000 8.1444 0.2960 0.1761 0.1008 15.0044 0.0815 0.0527 0.2082 -0.0690 0.1070 5.2075 0.7676 8.5000 8.5000 8.1438 0.2750 0.1659 0.1002 14.5625 0.0769 0.0475 0.1969 -0.0729 0.1027 5.3678 0.7269 8.5000 8.5000 8.1449 0.2536 0.1558 0.0997 14.1454 0.0725 0.0425 0.1856 -0.0768 0.0981 5.5281 0.6862 8.5000 8.5000 8.1473 0.2320 0.1458 0.0993 13.7510 0.0681 0.0379 0.1744 -0.0809 0.0933 5.6883 0.6458 8.5000 8.5000 8.1513 0.2101 0.1358 0.0989 13.3777 0.0639 0.0335 0.1632 -0.0852 0.0881 5.8486 0.6061 8.5000 8.5000 8.1569 0.1883 0.1259 0.0987 13.0238 0.0598 0.0296 0.1520 -0.0898 0.0827 6.0089 0.5673 8.5000 8.5000 8.1637 0.1664 0.1161 0.0986 12.6878 0.0559 0.0260 0.1408 -0.0947 0.0769 6.1692 0.5297 8.5000 8.5000 8.1723 0.1447 0.1063 0.0986 12.3684 0.0522 0.0227 0.1297 -0.0998 0.0709 6.3294 0.4937 8.5000 8.5000 8.1825 0.1232 0.0965 0.0986 12.0645 0.0487 0.0198 0.1187 -0.1054 0.0646 6.4897 0.4596 8.5000 8.5000 8.1943 0.1020 0.0867 0.0988 11.7750 0.0454 0.0172 0.1077 -0.1114 0.0580 6.6435 0.4289 8.5000 8.5000 8.1526 0.0821 0.0774 0.0991 11.5098 0.0425 0.0151 0.0964 -0.1177 0.0504 6.6854 0.4209 8.5000 8.5000 8.1170 0.0768 0.0748 0.0991 11.4396 0.0417 0.0145 0.0931 -0.1194 0.0479 6.7207 0.4142 8.5000 8.5000 8.0773 0.0722 0.0727 0.0992 11.3810 0.0411 0.0141 0.0901 -0.1210 0.0457 6.7561 0.4042 8.5000 8.5000 8.0276 0.0643 0.0698 0.0993 11.3230 0.0401 0.0135 0.0863 -0.1244 0.0430 6.7914 0.3894 8.5000 8.5000 7.9663 0.0515 0.0660 0.0994 11.2656 0.0387 0.0125 0.0813 -0.1304 0.0395 6.8268 0.3689 8.5000 8.5000 7.8664 0.0331 0.0611 0.0995 11.2087 0.0367 0.0112 0.0750 -0.1395 0.0352 6.8621 0.3414 8.5000 8.5000 7.6557 0.0076 0.0548 0.0996 11.1524 0.0340 0.0097 0.0670 -0.1524 0.0300 6.8975 0.3039 8.5000 8.5000 7.4753 -0.0277 0.0467 0.0997 11.0967 0.0303 0.0077 0.0569 -0.1707 0.0237 6.9328 0.2487 8.5000 8.5000 7.4251 -0.0805 0.0351 0.0998 11.0415 0.0248 0.0052 0.0430 -0.1983 0.0155 6.9682 0.1403 8.5000 8.5000 8.3951 -0.1857 0.0135 0.0999 10.9868 0.0140 0.0017 0.0177 -0.2540 0.0016 7.0000 0.0184 8.5000 8.5043 8.5043 -0.3044 -0.0103 0.1000 10.9435 0.0018 0.0000 -0.0103 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.82 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.085375 TOTAL WEIGHT (Kg) = 0.038719 TOTAL VOLUME (IN**3) = 1.390865 TOTAL PROJECTED AREA (IN**2) = 11.0458 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001754 MOMENT OF INERTIA (Kg-M**2) = 0.000198 STATIC MOMENT, ONE SIDE (IN-LB) = 0.095525 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 = 73.634 INNER LIMIT (NORMALIZED BY RADIUS) = 0.057 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 9360.39 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.82, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.12, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412