11x10 (11x10.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 2.2500 0.0000 0.0000 0.5000 0.0000 0.4753 0.0000 0.4753 0.0000 0.1000 0.0000 0.0000 0.1400 0.9555 3.0937 0.0188 -0.6401 0.4934 0.0083 0.4470 1.2240 0.4271 0.3738 0.1077 0.0111 -0.1150 0.2800 0.9097 3.8888 0.1462 -1.2350 0.4877 0.0309 0.4199 4.7494 0.3820 0.3702 0.1284 0.0300 -0.1080 0.4200 0.8700 4.6353 0.4778 -1.6378 0.4832 0.0639 0.3942 10.2618 0.3430 0.3610 0.1585 0.0509 -0.0955 0.5600 0.8442 5.3331 1.0927 -1.7095 0.4798 0.1037 0.3697 17.2524 0.3121 0.3462 0.1945 0.0729 -0.0786 0.7000 0.8369 5.9824 2.0424 -1.3405 0.4779 0.1468 0.3466 24.9085 0.2900 0.3272 0.2334 0.0950 -0.0589 0.8400 0.8476 6.5831 3.3303 -0.4716 0.4774 0.1899 0.3247 32.2513 0.2752 0.3053 0.2717 0.1164 -0.0378 0.9800 0.8702 7.1351 4.8850 0.8703 0.4787 0.2294 0.3041 38.4261 0.2646 0.2818 0.3060 0.1360 -0.0165 1.1200 0.8953 7.6385 6.5338 2.5323 0.4817 0.2618 0.2848 42.8759 0.2550 0.2579 0.3330 0.1530 0.0035 1.2600 0.9125 8.0934 7.9930 4.2091 0.4867 0.2836 0.2667 45.2745 0.2434 0.2339 0.3491 0.1667 0.0210 1.4000 0.9130 8.4996 8.8955 5.4593 0.4938 0.2913 0.2500 45.3209 0.2283 0.2096 0.3509 0.1765 0.0347 1.5393 0.9028 8.8556 9.2761 6.2203 0.5025 0.2885 0.2346 43.8034 0.2118 0.1862 0.3426 0.1838 0.0443 1.6671 0.8963 9.1397 9.5744 6.8750 0.5111 0.2846 0.2216 42.4294 0.1986 0.1682 0.3342 0.1900 0.0505 1.7941 0.8925 9.3822 9.8276 7.4795 0.5200 0.2794 0.2098 41.0816 0.1872 0.1529 0.3253 0.1957 0.0544 1.9212 0.8909 9.5846 10.0381 8.0289 0.5290 0.2730 0.1990 39.7457 0.1773 0.1398 0.3158 0.2007 0.0565 2.0483 0.8911 9.7470 10.2064 8.5157 0.5380 0.2655 0.1892 38.4164 0.1686 0.1288 0.3058 0.2050 0.0568 2.1753 0.8929 9.8693 10.3333 8.9332 0.5468 0.2569 0.1806 37.0899 0.1612 0.1195 0.2951 0.2085 0.0556 2.3024 0.8958 9.9516 10.4195 9.2762 0.5552 0.2473 0.1729 35.7634 0.1549 0.1118 0.2839 0.2112 0.0531 2.4295 0.8994 9.9938 10.4656 9.5402 0.5629 0.2365 0.1664 34.4346 0.1496 0.1054 0.2720 0.2131 0.0494 2.5566 0.9033 10.0000 10.4764 9.7259 0.5698 0.2248 0.1609 33.1122 0.1453 0.1004 0.2595 0.2142 0.0447 2.6836 0.9072 10.0000 10.4827 9.8605 0.5758 0.2121 0.1564 31.8686 0.1419 0.0967 0.2465 0.2147 0.0386 2.8107 0.9107 10.0000 10.4913 9.9501 0.5805 0.1984 0.1531 30.7131 0.1394 0.0941 0.2328 0.2147 0.0312 2.9378 0.9133 10.0000 10.5026 9.9947 0.5839 0.1838 0.1507 29.6392 0.1377 0.0926 0.2185 0.2141 0.0226 3.0648 0.9147 10.0000 10.5167 10.0000 0.5857 0.1683 0.1494 28.6401 0.1366 0.0919 0.2036 0.2127 0.0129 3.1919 0.9146 10.0000 10.5310 10.0002 0.5857 0.1523 0.1481 27.7038 0.1354 0.0910 0.1881 0.2105 0.0026 3.3190 0.9124 10.0000 10.5449 10.0003 0.5837 0.1357 0.1468 26.8240 0.1339 0.0897 0.1720 0.2074 -0.0082 3.4460 0.9078 10.0000 10.5585 10.0004 0.5796 0.1187 0.1455 25.9960 0.1321 0.0880 0.1553 0.2033 -0.0195 3.5731 0.9004 10.0000 10.5717 10.0004 0.5731 0.1012 0.1443 25.2153 0.1299 0.0858 0.1379 0.1982 -0.0312 3.7002 0.8898 10.0000 10.5844 10.0003 0.5640 0.0833 0.1430 24.4780 0.1272 0.0831 0.1200 0.1921 -0.0432 3.8272 0.8756 10.0000 10.5964 10.0003 0.5522 0.0650 0.1417 23.7806 0.1241 0.0797 0.1015 0.1849 -0.0554 3.9543 0.8574 10.0000 10.6077 10.0003 0.5375 0.0463 0.1405 23.1197 0.1204 0.0758 0.0823 0.1765 -0.0679 4.0814 0.8348 10.0000 10.6181 10.0003 0.5197 0.0272 0.1392 22.4923 0.1162 0.0712 0.0625 0.1670 -0.0805 4.2084 0.8074 10.0000 10.6274 10.0002 0.4985 0.0077 0.1379 21.8956 0.1114 0.0660 0.0421 0.1564 -0.0933 4.3355 0.7748 10.0000 10.6355 10.0002 0.4738 -0.0121 0.1366 21.3269 0.1059 0.0603 0.0211 0.1445 -0.1062 4.4626 0.7366 9.9951 10.6370 9.9953 0.4454 -0.0323 0.1354 20.7748 0.0997 0.0540 -0.0005 0.1314 -0.1191 4.5897 0.6923 9.9554 10.6014 9.9555 0.4131 -0.0528 0.1341 20.1846 0.0928 0.0473 -0.0228 0.1170 -0.1318 4.7167 0.6417 9.8756 10.5227 9.8757 0.3767 -0.0737 0.1328 19.5482 0.0852 0.0403 -0.0456 0.1012 -0.1443 4.8438 0.5843 9.7558 10.4159 9.7412 0.3360 -0.0946 0.1316 18.8929 0.0769 0.0331 -0.0690 0.0842 -0.1568 4.9709 0.5201 9.5959 10.3355 9.5303 0.2908 -0.1148 0.1303 18.3103 0.0678 0.0260 -0.0925 0.0658 -0.1692 5.0979 0.4485 9.3960 10.3102 9.2725 0.2409 -0.1342 0.1290 17.8424 0.0579 0.0192 -0.1161 0.0461 -0.1815 5.2198 0.3723 9.1666 10.3557 9.0110 0.1885 -0.1527 0.1278 17.5235 0.0476 0.0131 -0.1388 0.0260 -0.1930 5.2528 0.3504 9.0982 10.3803 8.9416 0.1735 -0.1578 0.1275 17.4591 0.0447 0.0116 -0.1451 0.0203 -0.1962 5.2806 0.3315 9.0385 10.4047 8.8843 0.1606 -0.1621 0.1272 17.4113 0.0422 0.0103 -0.1504 0.0155 -0.1988 5.3083 0.3121 8.9769 10.4321 8.8284 0.1475 -0.1665 0.1269 17.3684 0.0396 0.0091 -0.1557 0.0106 -0.2015 5.3361 0.2923 8.9134 10.4616 8.7742 0.1341 -0.1709 0.1266 17.3294 0.0370 0.0080 -0.1611 0.0057 -0.2041 5.3639 0.2720 8.8479 10.4922 8.7220 0.1205 -0.1755 0.1264 17.2924 0.0344 0.0069 -0.1666 0.0007 -0.2068 5.3917 0.2500 8.7806 10.5224 8.6722 0.1054 -0.1805 0.1261 17.2552 0.0315 0.0059 -0.1726 -0.0050 -0.2097 5.4194 0.2211 8.7113 10.5505 8.6350 0.0838 -0.1876 0.1258 17.2151 0.0278 0.0046 -0.1809 -0.0142 -0.2139 5.4472 0.1809 8.6401 10.5724 8.6918 0.0517 -0.1981 0.1255 17.1659 0.0227 0.0031 -0.1927 -0.0290 -0.2199 5.4750 0.1121 8.5670 10.5825 9.1614 -0.0075 -0.2169 0.1253 17.0993 0.0140 0.0012 -0.2136 -0.0584 -0.2308 5.5000 0.0082 8.4996 8.4996 8.4996 -0.1008 -0.2464 0.1250 13.8180 0.0010 0.0000 -0.2464 0.0000 0.0000 RADIUS: 5.50 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.40 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.096687 TOTAL WEIGHT (Kg) = 0.043849 TOTAL VOLUME (IN**3) = 1.575153 TOTAL PROJECTED AREA (IN**2) = 7.7256 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001079 MOMENT OF INERTIA (Kg-M**2) = 0.000122 STATIC MOMENT, ONE SIDE (IN-LB) = 0.077604 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 = 90.336 INNER LIMIT (NORMALIZED BY RADIUS) = 0.091 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 16023.49 BASED ON MODULUS (MILLION) = 1.60 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.