18x10E (18x10E.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 1.2500 0.9317 0.0000 0.0000 0.6250 0.0000 0.3000 0.0000 0.3750 0.0000 0.2350 0.0000 0.0000 0.2000 1.1876 2.7042 0.0247 -0.2845 0.6149 0.0189 0.2984 1.1270 0.3544 0.3866 0.2474 0.0239 0.0487 0.4000 1.1258 4.2841 0.1936 -0.4972 0.6052 0.0698 0.2938 4.4047 0.3307 0.3787 0.2794 0.0475 0.0673 0.6000 1.0742 5.6715 0.6368 -0.4288 0.5964 0.1447 0.2860 9.5884 0.3072 0.3546 0.3249 0.0726 0.0982 0.8000 1.0431 6.8664 1.4584 0.1010 0.5891 0.2357 0.2751 16.1795 0.2870 0.3214 0.3803 0.0973 0.1383 1.0000 1.0391 7.8686 2.7098 1.2108 0.5838 0.3351 0.2611 23.3294 0.2713 0.2848 0.4423 0.1200 0.1850 1.2000 1.0626 8.6784 4.3531 2.9032 0.5810 0.4351 0.2440 29.9999 0.2593 0.2492 0.5074 0.1395 0.2355 1.4000 1.1077 9.2955 6.2260 4.8988 0.5812 0.5280 0.2238 35.2902 0.2479 0.2178 0.5716 0.1544 0.2868 1.6000 1.1649 9.7201 8.0358 6.8978 0.5849 0.6060 0.2029 38.6365 0.2363 0.1925 0.6297 0.1636 0.3351 1.8000 1.2247 9.9521 9.4092 8.4702 0.5927 0.6612 0.1845 39.7589 0.2260 0.1750 0.6747 0.1654 0.3757 2.0000 1.2815 10.0000 9.9948 9.2356 0.6050 0.6860 0.1686 38.4975 0.2161 0.1672 0.6969 0.1571 0.4018 2.2010 1.3343 10.0000 10.0000 9.3642 0.6190 0.6863 0.1550 35.8709 0.2068 0.1667 0.6992 0.1402 0.4125 2.4190 1.3844 10.0000 10.0000 9.4679 0.6308 0.6776 0.1426 33.3428 0.1974 0.1667 0.6932 0.1214 0.4150 2.6379 1.4248 10.0000 10.0000 9.5530 0.6392 0.6603 0.1325 31.1039 0.1888 0.1665 0.6787 0.1029 0.4089 2.8569 1.4559 10.0000 10.0000 9.6177 0.6442 0.6407 0.1245 29.1218 0.1813 0.1664 0.6621 0.0850 0.4005 3.0759 1.4780 10.0000 10.0000 9.6623 0.6461 0.6208 0.1185 27.3585 0.1751 0.1664 0.6455 0.0677 0.3918 3.2948 1.4916 10.0000 10.0000 9.6871 0.6449 0.6006 0.1142 25.7826 0.1703 0.1668 0.6288 0.0512 0.3827 3.5138 1.4974 10.0000 10.0000 9.6936 0.6409 0.5804 0.1114 24.3678 0.1668 0.1674 0.6121 0.0356 0.3733 3.7328 1.4956 10.0000 10.0000 9.6836 0.6341 0.5600 0.1098 23.0921 0.1643 0.1682 0.5954 0.0210 0.3637 3.9517 1.4869 10.0000 10.0000 9.6670 0.6247 0.5400 0.1088 21.9370 0.1617 0.1681 0.5787 0.0072 0.3542 4.1707 1.4716 10.0000 10.0000 9.6446 0.6130 0.5203 0.1077 20.8870 0.1585 0.1664 0.5619 -0.0056 0.3449 4.3897 1.4504 10.0000 10.0000 9.6157 0.5989 0.5011 0.1068 19.9290 0.1548 0.1633 0.5452 -0.0174 0.3359 4.6086 1.4236 10.0000 10.0000 9.5852 0.5827 0.4824 0.1058 19.0519 0.1507 0.1587 0.5284 -0.0281 0.3272 4.8276 1.3917 10.0000 10.0000 9.5517 0.5646 0.4642 0.1050 18.2463 0.1461 0.1528 0.5115 -0.0376 0.3189 5.0466 1.3553 10.0000 10.0000 9.5191 0.5446 0.4464 0.1042 17.5039 0.1412 0.1457 0.4945 -0.0459 0.3110 5.2655 1.3148 10.0000 10.0000 9.4889 0.5230 0.4291 0.1035 16.8179 0.1360 0.1375 0.4775 -0.0532 0.3034 5.4845 1.2708 10.0000 10.0000 9.4618 0.4999 0.4122 0.1028 16.1823 0.1306 0.1285 0.4604 -0.0595 0.2961 5.7034 1.2236 10.0000 10.0000 9.4393 0.4754 0.3957 0.1022 15.5918 0.1250 0.1188 0.4433 -0.0649 0.2891 5.9224 1.1738 10.0000 10.0000 9.4206 0.4497 0.3795 0.1016 15.0419 0.1193 0.1090 0.4261 -0.0698 0.2820 6.1414 1.1218 10.0000 10.0000 9.4023 0.4229 0.3634 0.1011 14.5287 0.1134 0.0992 0.4088 -0.0745 0.2745 6.3603 1.0682 10.0000 10.0000 9.3841 0.3952 0.3474 0.1007 14.0486 0.1075 0.0897 0.3915 -0.0793 0.2666 6.5793 1.0134 10.0000 10.0000 9.3658 0.3668 0.3314 0.1003 13.5987 0.1016 0.0805 0.3741 -0.0841 0.2583 6.7983 0.9579 10.0000 10.0000 9.3476 0.3378 0.3156 0.1000 13.1763 0.0958 0.0718 0.3567 -0.0891 0.2495 7.0172 0.9022 10.0000 10.0000 9.3294 0.3083 0.2998 0.0997 12.7788 0.0900 0.0636 0.3391 -0.0944 0.2402 7.2362 0.8467 10.0000 10.0000 9.3111 0.2785 0.2839 0.0995 12.4043 0.0843 0.0560 0.3215 -0.0999 0.2304 7.4552 0.7921 10.0000 10.0000 9.2926 0.2486 0.2681 0.0994 12.0508 0.0787 0.0489 0.3038 -0.1059 0.2201 7.6741 0.7387 10.0000 10.0000 9.2738 0.2187 0.2522 0.0993 11.7165 0.0733 0.0425 0.2860 -0.1123 0.2094 7.8931 0.6870 10.0000 10.0000 9.2541 0.1889 0.2362 0.0993 11.4001 0.0682 0.0368 0.2682 -0.1192 0.1980 8.1121 0.6375 10.0000 10.0000 9.2329 0.1594 0.2201 0.0993 11.1002 0.0633 0.0317 0.2502 -0.1267 0.1861 8.3310 0.5907 10.0000 10.0000 9.2101 0.1304 0.2038 0.0994 10.8154 0.0587 0.0272 0.2322 -0.1348 0.1737 8.5410 0.5489 10.0000 10.0000 9.1801 0.1032 0.1881 0.0995 10.5556 0.0546 0.0235 0.2147 -0.1433 0.1611 8.5955 0.5385 10.0000 10.0000 9.1476 0.0962 0.1840 0.0996 10.4902 0.0536 0.0227 0.2098 -0.1457 0.1573 8.6409 0.5299 10.0000 10.0000 9.1020 0.0903 0.1805 0.0996 10.4362 0.0528 0.0220 0.2054 -0.1477 0.1538 8.6864 0.5172 10.0000 10.0000 9.0390 0.0802 0.1762 0.0997 10.3828 0.0516 0.0209 0.1999 -0.1521 0.1496 8.7318 0.4983 10.0000 10.0000 8.9562 0.0639 0.1708 0.0997 10.3299 0.0497 0.0194 0.1928 -0.1599 0.1443 8.7773 0.4721 10.0000 10.0000 8.8152 0.0403 0.1641 0.0998 10.2776 0.0471 0.0174 0.1839 -0.1719 0.1379 8.8227 0.4370 10.0000 10.0000 8.4245 0.0077 0.1558 0.0998 10.2257 0.0436 0.0150 0.1731 -0.1888 0.1304 8.8682 0.3890 10.0000 10.0000 7.9973 -0.0377 0.1452 0.0999 10.1744 0.0389 0.0119 0.1596 -0.2128 0.1214 8.9136 0.3185 10.0000 10.0000 7.5827 -0.1054 0.1307 0.0999 10.1236 0.0318 0.0080 0.1416 -0.2492 0.1100 8.9591 0.1798 10.0000 10.0000 7.6284 -0.2404 0.1043 0.1000 10.0733 0.0180 0.0026 0.1100 -0.3226 0.0917 9.0000 0.0235 10.0000 10.0051 10.0050 -0.3931 0.0754 0.1000 10.0334 0.0023 0.0000 0.0754 0.0000 0.0000 RADIUS: 9.00 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 2.00 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.164515 TOTAL WEIGHT (Kg) = 0.074610 TOTAL VOLUME (IN**3) = 2.680168 TOTAL PROJECTED AREA (IN**2) = 18.7619 MOMENT OF INERTIA (SNAIL-IN**2) = 0.005895 MOMENT OF INERTIA (Kg-M**2) = 0.000666 STATIC MOMENT, ONE SIDE (IN-LB) = 0.244632 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 = 73.406 INNER LIMIT (NORMALIZED BY RADIUS) = 0.069 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 6155.22 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.76, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412