14x4W (14x4W.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 1.0000 3.6265 0.0000 0.0000 0.5000 0.0000 0.2139 0.0000 0.2139 0.0000 0.1300 0.0000 0.0000 0.1600 0.9603 3.4003 0.0101 -0.5196 0.4948 0.0009 0.2080 0.5729 0.1998 0.3139 0.1293 0.0119 -0.0598 0.3200 0.9362 3.1995 0.0759 -0.9710 0.4945 0.0034 0.2024 2.1624 0.1895 0.3029 0.1272 0.0246 -0.0630 0.4800 0.9266 3.0239 0.2369 -1.2205 0.4981 0.0069 0.1970 4.4904 0.1826 0.2865 0.1236 0.0361 -0.0668 0.6400 0.9305 2.8737 0.5092 -1.1879 0.5047 0.0112 0.1919 7.2172 0.1786 0.2664 0.1195 0.0465 -0.0702 0.8000 0.9460 2.7488 0.8850 -0.8574 0.5135 0.0158 0.1870 9.9850 0.1769 0.2438 0.1157 0.0560 -0.0726 0.9600 0.9702 2.6492 1.3342 -0.2742 0.5235 0.0203 0.1823 12.4729 0.1769 0.2203 0.1127 0.0651 -0.0730 1.1200 0.9996 2.5749 1.8106 0.4670 0.5339 0.0243 0.1779 14.4285 0.1778 0.1973 0.1108 0.0738 -0.0709 1.2800 1.0304 2.5259 2.2558 1.2357 0.5437 0.0275 0.1737 15.6680 0.1790 0.1769 0.1100 0.0818 -0.0660 1.4400 1.0588 2.5023 2.6035 1.8757 0.5521 0.0294 0.1698 16.0533 0.1797 0.1615 0.1102 0.0876 -0.0587 1.6000 1.0813 2.5039 2.7803 2.2104 0.5581 0.0297 0.1661 15.4594 0.1795 0.1541 0.1112 0.0877 -0.0505 1.7604 1.0994 2.5310 2.8310 2.2872 0.5628 0.0289 0.1626 14.3559 0.1787 0.1533 0.1126 0.0831 -0.0432 1.9286 1.1186 2.5867 2.9095 2.3858 0.5687 0.0281 0.1592 13.5009 0.1781 0.1532 0.1135 0.0795 -0.0380 2.0972 1.1379 2.6707 3.0158 2.5075 0.5754 0.0273 0.1560 12.8910 0.1776 0.1536 0.1138 0.0772 -0.0348 2.2659 1.1569 2.7827 3.1500 2.6532 0.5827 0.0265 0.1532 12.4763 0.1772 0.1544 0.1134 0.0758 -0.0333 2.4345 1.1755 2.9229 3.3122 2.8235 0.5903 0.0254 0.1506 12.2179 0.1770 0.1555 0.1124 0.0752 -0.0333 2.6031 1.1932 3.0858 3.4970 3.0134 0.5981 0.0240 0.1482 12.0687 0.1769 0.1567 0.1108 0.0752 -0.0346 2.7717 1.2099 3.2422 3.6754 3.1941 0.6058 0.0218 0.1461 11.9171 0.1768 0.1580 0.1085 0.0756 -0.0365 2.9403 1.2252 3.3876 3.8430 3.3598 0.6131 0.0188 0.1443 11.7506 0.1768 0.1593 0.1057 0.0763 -0.0390 3.1090 1.2389 3.5220 3.9998 3.5097 0.6199 0.0151 0.1428 11.5720 0.1769 0.1606 0.1022 0.0771 -0.0420 3.2776 1.2506 3.6454 4.1462 3.6426 0.6260 0.0106 0.1415 11.3833 0.1770 0.1619 0.0981 0.0779 -0.0456 3.4462 1.2602 3.7578 4.2821 3.7578 0.6310 0.0053 0.1405 11.1864 0.1770 0.1631 0.0933 0.0787 -0.0497 3.6148 1.2673 3.8592 4.4076 3.8592 0.6348 -0.0007 0.1397 10.9824 0.1771 0.1639 0.0880 0.0794 -0.0543 3.7834 1.2716 3.9496 4.5221 3.9496 0.6371 -0.0071 0.1390 10.7704 0.1767 0.1641 0.0820 0.0798 -0.0591 3.9521 1.2728 4.0290 4.6251 4.0290 0.6377 -0.0141 0.1383 10.5510 0.1760 0.1636 0.0754 0.0798 -0.0642 4.1207 1.2708 4.0974 4.7169 4.0974 0.6365 -0.0214 0.1375 10.3250 0.1748 0.1622 0.0682 0.0794 -0.0696 4.2893 1.2651 4.1549 4.7972 4.1548 0.6330 -0.0292 0.1368 10.0929 0.1730 0.1598 0.0603 0.0784 -0.0751 4.4579 1.2555 4.2013 4.8661 4.2012 0.6273 -0.0373 0.1361 9.8554 0.1708 0.1566 0.0518 0.0767 -0.0809 4.6266 1.2417 4.2367 4.9235 4.2366 0.6189 -0.0458 0.1353 9.6130 0.1680 0.1523 0.0427 0.0743 -0.0869 4.7952 1.2235 4.2611 4.9694 4.2610 0.6077 -0.0546 0.1346 9.3659 0.1647 0.1471 0.0330 0.0709 -0.0931 4.9638 1.2005 4.2746 5.0037 4.2744 0.5935 -0.0637 0.1339 9.1146 0.1607 0.1408 0.0226 0.0666 -0.0994 5.1324 1.1726 4.2770 5.0264 4.2768 0.5759 -0.0731 0.1331 8.8593 0.1561 0.1336 0.0116 0.0612 -0.1059 5.3010 1.1393 4.2684 5.0374 4.2683 0.5549 -0.0827 0.1324 8.6002 0.1508 0.1255 0.0000 0.0547 -0.1127 5.4697 1.1004 4.2488 5.0365 4.2487 0.5302 -0.0925 0.1317 8.3374 0.1449 0.1164 -0.0122 0.0468 -0.1195 5.6383 1.0556 4.2183 5.0236 4.2182 0.5015 -0.1025 0.1309 8.0709 0.1382 0.1066 -0.0251 0.0375 -0.1266 5.8069 1.0047 4.1767 4.9985 4.1766 0.4686 -0.1127 0.1302 7.8008 0.1308 0.0961 -0.0385 0.0268 -0.1338 5.9755 0.9474 4.1241 4.9608 4.1241 0.4313 -0.1230 0.1295 7.5269 0.1227 0.0850 -0.0526 0.0144 -0.1412 6.1441 0.8833 4.0606 4.9102 4.0605 0.3894 -0.1333 0.1287 7.2487 0.1137 0.0735 -0.0674 0.0004 -0.1488 6.3128 0.8123 3.9858 4.8458 3.9858 0.3427 -0.1438 0.1280 6.9653 0.1040 0.0619 -0.0827 -0.0155 -0.1565 6.4814 0.7340 3.8877 4.7544 3.8877 0.2908 -0.1543 0.1273 6.6590 0.0934 0.0503 -0.0987 -0.0332 -0.1643 6.6431 0.6518 3.7656 4.6336 3.7656 0.2361 -0.1644 0.1266 6.3346 0.0825 0.0395 -0.1146 -0.0522 -0.1720 6.6854 0.6271 3.7291 4.5968 3.7296 0.2190 -0.1673 0.1264 6.2452 0.0793 0.0366 -0.1192 -0.0585 -0.1742 6.7207 0.6024 3.6972 4.5649 3.6989 0.2007 -0.1700 0.1262 6.1699 0.0760 0.0337 -0.1238 -0.0660 -0.1764 6.7561 0.5733 3.6639 4.5319 3.6693 0.1782 -0.1732 0.1261 6.0938 0.0723 0.0305 -0.1291 -0.0758 -0.1790 6.7914 0.5390 3.6293 4.4976 3.6461 0.1506 -0.1768 0.1259 6.0167 0.0679 0.0270 -0.1353 -0.0884 -0.1821 6.8268 0.4982 3.5934 4.4618 3.6213 0.1166 -0.1811 0.1258 5.9385 0.0627 0.0230 -0.1426 -0.1045 -0.1857 6.8621 0.4484 3.5562 4.4245 3.6067 0.0738 -0.1861 0.1256 5.8590 0.0563 0.0187 -0.1514 -0.1255 -0.1901 6.8975 0.3844 3.5177 4.3857 3.6061 0.0169 -0.1925 0.1255 5.7785 0.0482 0.0137 -0.1627 -0.1544 -0.1957 6.9328 0.2875 3.4778 4.3473 3.6706 -0.0726 -0.2019 0.1253 5.6992 0.0360 0.0077 -0.1796 -0.2013 -0.2043 6.9682 0.1479 3.4367 4.3101 4.0247 -0.2045 -0.2153 0.1252 5.6223 0.0185 0.0021 -0.2037 -0.2718 -0.2166 7.0000 0.0222 3.3985 3.3985 3.3985 -0.3233 -0.2273 0.1250 4.4184 0.0028 0.0000 -0.2273 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.60 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.132339 TOTAL WEIGHT (Kg) = 0.060018 TOTAL VOLUME (IN**3) = 2.155979 TOTAL PROJECTED AREA (IN**2) = 14.6451 MOMENT OF INERTIA (SNAIL-IN**2) = 0.003781 MOMENT OF INERTIA (Kg-M**2) = 0.000427 STATIC MOMENT, ONE SIDE (IN-LB) = 0.181111 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 = 105.090 INNER LIMIT (NORMALIZED BY RADIUS) = 0.071 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 8222.53 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.