16x10 (16x10.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 -1.5740 0.0000 0.0000 0.6250 0.0000 0.4913 0.0000 0.6142 0.0000 0.1600 0.0000 0.0000 0.1920 1.1941 -0.1399 0.0217 -1.0308 0.6184 0.0058 0.4591 1.0285 0.5482 0.6883 0.1646 0.0159 -0.1651 0.3840 1.1443 1.1993 0.1676 -1.9750 0.6174 0.0215 0.4284 3.9743 0.4902 0.6648 0.1767 0.0416 -0.1616 0.5760 1.1061 2.4438 0.5422 -2.6104 0.6211 0.0446 0.3993 8.5200 0.4416 0.6314 0.1942 0.0709 -0.1549 0.7680 1.0851 3.5934 1.2198 -2.7538 0.6289 0.0728 0.3717 14.1859 0.4033 0.5912 0.2152 0.1022 -0.1454 0.9600 1.0842 4.6482 2.2320 -2.2914 0.6399 0.1036 0.3457 20.3065 0.3748 0.5476 0.2378 0.1341 -0.1335 1.1520 1.1022 5.6082 3.5535 -1.2036 0.6536 0.1349 0.3212 26.1480 0.3540 0.5033 0.2602 0.1652 -0.1195 1.3440 1.1335 6.4734 5.0901 0.4098 0.6690 0.1642 0.2982 31.0800 0.3380 0.4603 0.2803 0.1942 -0.1043 1.5360 1.1696 7.2437 6.6751 2.3162 0.6855 0.1892 0.2769 34.6695 0.3238 0.4203 0.2960 0.2197 -0.0887 1.7280 1.2015 7.9193 8.0770 4.1558 0.7024 0.2075 0.2570 36.6464 0.3088 0.3842 0.3052 0.2403 -0.0741 1.9200 1.2211 8.5000 9.0225 5.4737 0.7189 0.2169 0.2387 36.7931 0.2915 0.3530 0.3057 0.2544 -0.0624 2.1119 1.2313 8.9856 9.5318 6.2480 0.7350 0.2192 0.2220 35.6914 0.2734 0.3258 0.2998 0.2635 -0.0535 2.3012 1.2417 9.3721 9.9324 6.9508 0.7511 0.2195 0.2070 34.4865 0.2571 0.3011 0.2932 0.2717 -0.0456 2.4905 1.2522 9.6661 10.2356 7.5796 0.7673 0.2180 0.1936 33.1892 0.2424 0.2783 0.2861 0.2791 -0.0384 2.6797 1.2626 9.8681 10.4430 8.1199 0.7832 0.2148 0.1816 31.8086 0.2293 0.2577 0.2783 0.2858 -0.0319 2.8690 1.2725 9.9779 10.5559 8.5586 0.7987 0.2099 0.1711 30.3527 0.2178 0.2392 0.2699 0.2918 -0.0259 3.0582 1.2817 10.0000 10.5803 8.8886 0.8136 0.2035 0.1622 28.8380 0.2079 0.2229 0.2609 0.2970 -0.0205 3.2474 1.2899 10.0000 10.5839 9.1614 0.8275 0.1957 0.1547 27.4162 0.1996 0.2090 0.2512 0.3022 -0.0168 3.4367 1.2967 10.0000 10.5903 9.3959 0.8403 0.1866 0.1488 26.1254 0.1929 0.1976 0.2410 0.3074 -0.0151 3.6259 1.3019 10.0000 10.6007 9.5920 0.8518 0.1762 0.1443 24.9526 0.1879 0.1885 0.2301 0.3124 -0.0153 3.8152 1.3052 10.0000 10.6159 9.7498 0.8617 0.1644 0.1414 23.8865 0.1846 0.1819 0.2185 0.3171 -0.0172 4.0044 1.3062 10.0000 10.6371 9.8691 0.8697 0.1512 0.1400 22.9172 0.1829 0.1776 0.2063 0.3215 -0.0209 4.1937 1.3048 10.0000 10.6614 9.9502 0.8758 0.1370 0.1393 22.0290 0.1817 0.1744 0.1935 0.3253 -0.0260 4.3829 1.3006 10.0000 10.6855 9.9929 0.8795 0.1224 0.1386 21.2073 0.1802 0.1715 0.1800 0.3285 -0.0322 4.5721 1.2932 10.0000 10.7094 10.0000 0.8808 0.1074 0.1379 20.4451 0.1783 0.1685 0.1659 0.3310 -0.0393 4.7614 1.2825 10.0000 10.7331 10.0001 0.8793 0.0920 0.1371 19.7363 0.1759 0.1648 0.1512 0.3325 -0.0470 4.9506 1.2679 10.0000 10.7564 10.0001 0.8748 0.0762 0.1364 19.0755 0.1730 0.1602 0.1358 0.3328 -0.0553 5.1399 1.2494 10.0000 10.7793 10.0001 0.8672 0.0601 0.1357 18.4580 0.1696 0.1547 0.1198 0.3318 -0.0641 5.3291 1.2265 10.0000 10.8017 10.0001 0.8561 0.0436 0.1350 17.8795 0.1656 0.1483 0.1032 0.3294 -0.0733 5.5183 1.1989 10.0000 10.8236 10.0001 0.8414 0.0268 0.1343 17.3364 0.1610 0.1410 0.0859 0.3255 -0.0829 5.7076 1.1664 10.0000 10.8447 10.0000 0.8228 0.0097 0.1336 16.8254 0.1558 0.1328 0.0679 0.3200 -0.0929 5.8968 1.1286 10.0000 10.8650 10.0000 0.8001 -0.0076 0.1329 16.3435 0.1500 0.1237 0.0494 0.3127 -0.1032 6.0861 1.0852 10.0000 10.8842 10.0000 0.7731 -0.0253 0.1322 15.8880 0.1434 0.1138 0.0302 0.3037 -0.1137 6.2753 1.0359 10.0000 10.9023 10.0000 0.7415 -0.0432 0.1315 15.4564 0.1362 0.1032 0.0103 0.2926 -0.1246 6.4646 0.9804 10.0000 10.9187 10.0000 0.7051 -0.0613 0.1308 15.0463 0.1282 0.0920 -0.0102 0.2796 -0.1356 6.6538 0.9184 10.0000 10.9332 10.0000 0.6636 -0.0796 0.1300 14.6555 0.1194 0.0803 -0.0313 0.2644 -0.1468 6.8430 0.8496 10.0000 10.9449 10.0000 0.6169 -0.0981 0.1293 14.2817 0.1099 0.0684 -0.0531 0.2470 -0.1582 7.0323 0.7737 9.9886 10.9415 9.9886 0.5648 -0.1168 0.1286 13.9083 0.0995 0.0565 -0.0755 0.2272 -0.1697 7.2215 0.6903 9.8942 10.8494 9.8942 0.5069 -0.1358 0.1279 13.4475 0.0883 0.0448 -0.0985 0.2049 -0.1810 7.4108 0.5991 9.7041 10.6531 9.7042 0.4430 -0.1551 0.1272 12.8868 0.0762 0.0336 -0.1222 0.1800 -0.1922 7.5922 0.5041 9.4321 10.3616 9.4321 0.3760 -0.1738 0.1265 12.2547 0.0638 0.0238 -0.1456 0.1537 -0.2029 7.6404 0.4776 9.3451 10.2660 9.3451 0.3572 -0.1788 0.1263 12.0708 0.0603 0.0213 -0.1518 0.1463 -0.2058 7.6808 0.4550 9.2674 10.1796 9.2674 0.3412 -0.1829 0.1262 11.9109 0.0574 0.0194 -0.1572 0.1400 -0.2083 7.7212 0.4320 9.1853 10.0871 9.1853 0.3248 -0.1871 0.1260 11.7458 0.0544 0.0175 -0.1625 0.1335 -0.2107 7.7616 0.4085 9.0988 9.9883 9.0988 0.3081 -0.1913 0.1259 11.5749 0.0514 0.0156 -0.1679 0.1269 -0.2132 7.8020 0.3846 9.0080 9.8828 9.0080 0.2910 -0.1955 0.1257 11.3982 0.0484 0.0139 -0.1733 0.1201 -0.2157 7.8424 0.3549 8.9128 9.7711 8.9139 0.2684 -0.2007 0.1256 11.2160 0.0446 0.0118 -0.1801 0.1104 -0.2189 7.8828 0.3150 8.8133 9.6525 8.8327 0.2358 -0.2077 0.1254 11.0278 0.0395 0.0093 -0.1893 0.0951 -0.2236 7.9232 0.2586 8.7094 9.5258 8.7951 0.1871 -0.2177 0.1253 10.8323 0.0324 0.0063 -0.2025 0.0711 -0.2305 7.9636 0.1573 8.6011 9.3910 9.0010 0.0943 -0.2356 0.1251 10.6297 0.0197 0.0024 -0.2263 0.0228 -0.2434 8.0000 0.0131 8.5000 8.5001 8.5000 -0.0414 -0.2609 0.1250 9.5981 0.0016 0.0000 -0.2609 0.0000 0.0000 RADIUS: 8.00 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 1.92 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.241612 TOTAL WEIGHT (Kg) = 0.109575 TOTAL VOLUME (IN**3) = 3.936165 TOTAL PROJECTED AREA (IN**2) = 16.1861 MOMENT OF INERTIA (SNAIL-IN**2) = 0.005802 MOMENT OF INERTIA (Kg-M**2) = 0.000655 STATIC MOMENT, ONE SIDE (IN-LB) = 0.284405 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 = 84.494 INNER LIMIT (NORMALIZED BY RADIUS) = 0.078 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 12912.80 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.