16x14 (16x14.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 -4.6445 0.0000 0.0000 0.6250 0.0000 0.4913 0.0000 0.6142 0.0000 0.1600 0.0000 0.0000 0.1920 1.1931 -2.6550 0.0227 -1.0327 0.6184 0.0071 0.4591 1.0772 0.5477 0.6884 0.1656 0.0164 -0.1644 0.3840 1.1405 -0.7778 0.1765 -1.9838 0.6174 0.0263 0.4284 4.1842 0.4886 0.6652 0.1807 0.0435 -0.1590 0.5760 1.0987 0.9872 0.5753 -2.6296 0.6211 0.0545 0.3993 9.0322 0.4387 0.6323 0.2026 0.0748 -0.1495 0.7680 1.0743 2.6401 1.3070 -2.7782 0.6289 0.0889 0.3717 15.1555 0.3993 0.5926 0.2287 0.1085 -0.1366 0.9600 1.0715 4.1807 2.4206 -2.2977 0.6399 0.1265 0.3457 21.8654 0.3704 0.5494 0.2569 0.1432 -0.1216 1.1520 1.0895 5.6091 3.9087 -1.1436 0.6536 0.1645 0.3212 28.3694 0.3499 0.5054 0.2846 0.1774 -0.1053 1.3440 1.1228 6.9252 5.6910 0.6098 0.6690 0.1999 0.2982 33.9771 0.3349 0.4628 0.3095 0.2095 -0.0891 1.5360 1.1621 8.1292 7.6021 2.7446 0.6855 0.2299 0.2769 38.2276 0.3217 0.4233 0.3290 0.2383 -0.0744 1.7280 1.1972 9.2209 9.3919 4.8923 0.7024 0.2517 0.2570 40.8608 0.3077 0.3878 0.3404 0.2621 -0.0628 1.9200 1.2185 10.2005 10.7459 6.5575 0.7189 0.2623 0.2387 41.6934 0.2909 0.3572 0.3412 0.2796 -0.0562 2.1119 1.2288 11.0672 11.6440 7.6834 0.7350 0.2641 0.2220 41.2677 0.2728 0.3304 0.3342 0.2920 -0.0538 2.3012 1.2393 11.8129 12.4107 8.7494 0.7511 0.2637 0.2070 40.6405 0.2566 0.3059 0.3267 0.3028 -0.0519 2.4905 1.2501 12.4489 13.0618 9.7509 0.7673 0.2615 0.1936 39.8525 0.2420 0.2833 0.3184 0.3124 -0.0505 2.6797 1.2606 12.9759 13.5990 10.6674 0.7832 0.2575 0.1816 38.9269 0.2289 0.2626 0.3096 0.3206 -0.0494 2.8690 1.2708 13.3939 14.0234 11.4800 0.7987 0.2520 0.1711 37.8809 0.2175 0.2439 0.3001 0.3276 -0.0487 3.0582 1.2802 13.7029 14.3366 12.1724 0.8136 0.2448 0.1622 36.7267 0.2076 0.2272 0.2900 0.3334 -0.0482 3.2474 1.2885 13.9029 14.5400 12.7308 0.8275 0.2362 0.1547 35.4735 0.1994 0.2127 0.2792 0.3379 -0.0479 3.4367 1.2955 13.9939 14.6353 13.1437 0.8403 0.2261 0.1488 34.1281 0.1927 0.2005 0.2678 0.3413 -0.0477 3.6259 1.3009 14.0000 14.6483 13.4254 0.8518 0.2146 0.1443 32.7396 0.1878 0.1907 0.2558 0.3438 -0.0479 3.8152 1.3043 14.0000 14.6602 13.6475 0.8617 0.2017 0.1414 31.4487 0.1844 0.1833 0.2432 0.3461 -0.0495 4.0044 1.3055 14.0000 14.6784 13.8156 0.8697 0.1876 0.1400 30.2589 0.1827 0.1784 0.2299 0.3481 -0.0525 4.1937 1.3041 14.0000 14.6997 13.9297 0.8758 0.1725 0.1393 29.1561 0.1816 0.1748 0.2160 0.3498 -0.0568 4.3829 1.2999 14.0000 14.7211 13.9899 0.8795 0.1570 0.1386 28.1273 0.1801 0.1716 0.2014 0.3511 -0.0622 4.5721 1.2926 14.0000 14.7423 14.0000 0.8808 0.1409 0.1379 27.1657 0.1782 0.1686 0.1862 0.3518 -0.0684 4.7614 1.2819 14.0000 14.7632 14.0002 0.8793 0.1244 0.1371 26.2654 0.1758 0.1649 0.1704 0.3516 -0.0753 4.9506 1.2675 14.0000 14.7839 14.0003 0.8748 0.1075 0.1364 25.4208 0.1729 0.1603 0.1539 0.3504 -0.0827 5.1399 1.2490 14.0000 14.8042 14.0004 0.8672 0.0902 0.1357 24.6272 0.1695 0.1549 0.1368 0.3480 -0.0905 5.3291 1.2261 14.0000 14.8240 14.0003 0.8561 0.0724 0.1350 23.8800 0.1655 0.1485 0.1190 0.3442 -0.0986 5.5183 1.1986 14.0000 14.8432 14.0003 0.8414 0.0542 0.1343 23.1754 0.1610 0.1411 0.1006 0.3390 -0.1072 5.7076 1.1661 14.0000 14.8616 14.0003 0.8228 0.0357 0.1336 22.5097 0.1558 0.1329 0.0816 0.3322 -0.1160 5.8968 1.1283 14.0000 14.8791 14.0003 0.8001 0.0168 0.1329 21.8797 0.1499 0.1238 0.0619 0.3238 -0.1251 6.0861 1.0850 14.0000 14.8954 14.0002 0.7731 -0.0024 0.1322 21.2822 0.1434 0.1139 0.0416 0.3136 -0.1345 6.2753 1.0357 14.0000 14.9102 14.0002 0.7415 -0.0219 0.1315 20.7144 0.1362 0.1033 0.0206 0.3015 -0.1440 6.4646 0.9802 14.0000 14.9232 14.0002 0.7051 -0.0418 0.1308 20.1736 0.1282 0.0921 -0.0010 0.2874 -0.1538 6.6538 0.9183 14.0000 14.9338 14.0001 0.6636 -0.0619 0.1300 19.6571 0.1194 0.0805 -0.0233 0.2712 -0.1637 6.8430 0.8495 14.0000 14.9410 14.0001 0.6169 -0.0823 0.1293 19.1622 0.1099 0.0686 -0.0462 0.2528 -0.1738 7.0323 0.7735 13.9841 14.9277 13.9842 0.5648 -0.1029 0.1286 18.6672 0.0995 0.0566 -0.0697 0.2320 -0.1838 7.2215 0.6901 13.8519 14.7906 13.8520 0.5069 -0.1240 0.1279 18.0544 0.0883 0.0449 -0.0939 0.2088 -0.1935 7.4108 0.5995 13.5858 14.6301 13.5348 0.4430 -0.1440 0.1272 17.4427 0.0763 0.0338 -0.1181 0.1829 -0.2029 7.5922 0.5059 13.2049 14.7171 13.0448 0.3760 -0.1599 0.1265 17.1456 0.0640 0.0239 -0.1400 0.1556 -0.2117 7.6404 0.4798 13.0831 14.7930 12.8996 0.3572 -0.1638 0.1263 17.1266 0.0606 0.0214 -0.1457 0.1480 -0.2139 7.6808 0.4576 12.9743 14.8758 12.7763 0.3412 -0.1670 0.1262 17.1316 0.0577 0.0195 -0.1504 0.1415 -0.2158 7.7212 0.4350 12.8594 14.9766 12.6530 0.3248 -0.1702 0.1260 17.1559 0.0548 0.0176 -0.1550 0.1348 -0.2177 7.7616 0.4120 12.7383 15.0956 12.5309 0.3081 -0.1734 0.1259 17.1995 0.0519 0.0157 -0.1597 0.1280 -0.2195 7.8020 0.3884 12.6112 15.2328 12.4114 0.2911 -0.1767 0.1257 17.2620 0.0488 0.0139 -0.1644 0.1211 -0.2214 7.8424 0.3595 12.4779 15.3884 12.2965 0.2690 -0.1816 0.1256 17.3432 0.0451 0.0119 -0.1708 0.1115 -0.2242 7.8828 0.3199 12.3386 15.5613 12.2226 0.2369 -0.1897 0.1254 17.4419 0.0401 0.0094 -0.1807 0.0964 -0.2288 7.9232 0.2636 12.1932 15.7491 12.2622 0.1889 -0.2029 0.1253 17.5549 0.0330 0.0064 -0.1960 0.0727 -0.2363 7.9636 0.1616 12.0416 15.9491 12.8511 0.0976 -0.2303 0.1251 17.6795 0.0202 0.0024 -0.2263 0.0254 -0.2517 8.0000 0.0131 11.9000 11.8999 11.9000 -0.0381 -0.2737 0.1250 13.3191 0.0016 0.0000 -0.2737 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) = 0.241633 TOTAL WEIGHT (Kg) = 0.109584 TOTAL VOLUME (IN**3) = 3.959810 TOTAL PROJECTED AREA (IN**2) = 15.4355 MOMENT OF INERTIA (SNAIL-IN**2) = 0.005797 MOMENT OF INERTIA (Kg-M**2) = 0.000655 STATIC MOMENT, ONE SIDE (IN-LB) = 0.284547 SANITY CHECK DATA ARE BELOW DENSITY (SPECIFIC GRAVITY, INPUT FILE) = 1.690 DENSITY (INPUT FILE, LB/IN**3) = 0.6102E-01 AVERAGE DENSITY (FROM WT & VOL ABOVE, LB/IN**3) = 0.6102E-01 ACTIVITY FACTOR = 84.494 INNER LIMIT (NORMALIZED BY RADIUS) = 0.078 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 12891.56 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.69 ----- 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.