11x6 (11x6.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 1.3513 0.0000 0.0000 0.5000 0.0000 0.3902 0.0000 0.3902 0.0000 0.1250 0.0000 0.0000 0.1400 0.9598 1.8573 0.0144 -0.6153 0.4934 0.0041 0.3713 0.9364 0.3564 0.3834 0.1281 0.0096 -0.1009 0.2800 0.9248 2.3343 0.1102 -1.1722 0.4877 0.0153 0.3533 3.5855 0.3267 0.3749 0.1363 0.0228 -0.1001 0.4200 0.8979 2.7820 0.3526 -1.5288 0.4832 0.0314 0.3360 7.6095 0.3017 0.3594 0.1477 0.0363 -0.0977 0.5600 0.8822 3.2006 0.7839 -1.5722 0.4798 0.0507 0.3195 12.5591 0.2819 0.3382 0.1610 0.0499 -0.0936 0.7000 0.8788 3.5901 1.4177 -1.2390 0.4779 0.0713 0.3039 17.8663 0.2670 0.3135 0.1751 0.0635 -0.0878 0.8400 0.8861 3.9504 2.2324 -0.5269 0.4774 0.0915 0.2890 22.9274 0.2561 0.2869 0.1889 0.0769 -0.0802 0.9800 0.9002 4.2815 3.1662 0.4952 0.4787 0.1095 0.2749 27.2119 0.2475 0.2600 0.2006 0.0900 -0.0711 1.1200 0.9151 4.5835 4.1151 1.6814 0.4817 0.1235 0.2616 30.3177 0.2394 0.2340 0.2088 0.1026 -0.0610 1.2600 0.9243 4.8563 4.9355 2.8090 0.4867 0.1316 0.2491 31.9405 0.2303 0.2098 0.2117 0.1144 -0.0509 1.4000 0.9225 5.1000 5.4505 3.5878 0.4938 0.1320 0.2374 31.7833 0.2190 0.1887 0.2074 0.1245 -0.0422 1.5393 0.9139 5.3136 5.6848 4.0040 0.5025 0.1268 0.2266 30.4456 0.2070 0.1710 0.1981 0.1331 -0.0361 1.6671 0.9087 5.4840 5.8701 4.3589 0.5111 0.1212 0.2173 29.2671 0.1974 0.1574 0.1892 0.1406 -0.0326 1.7941 0.9058 5.6294 6.0288 4.6845 0.5200 0.1148 0.2087 28.1382 0.1891 0.1461 0.1802 0.1478 -0.0307 1.9212 0.9049 5.7508 6.1624 4.9785 0.5290 0.1078 0.2008 27.0441 0.1817 0.1365 0.1708 0.1545 -0.0302 2.0483 0.9055 5.8482 6.2709 5.2372 0.5380 0.1002 0.1936 25.9783 0.1753 0.1285 0.1613 0.1607 -0.0309 2.1753 0.9074 5.9216 6.3549 5.4573 0.5468 0.0918 0.1870 24.9358 0.1697 0.1217 0.1514 0.1664 -0.0328 2.3024 0.9102 5.9710 6.4146 5.6361 0.5552 0.0829 0.1810 23.9129 0.1647 0.1161 0.1413 0.1714 -0.0356 2.4295 0.9134 5.9963 6.4502 5.7716 0.5629 0.0733 0.1757 22.9066 0.1605 0.1115 0.1309 0.1757 -0.0392 2.5566 0.9168 6.0000 6.4645 5.8643 0.5698 0.0632 0.1711 21.9219 0.1568 0.1078 0.1203 0.1793 -0.0435 2.6836 0.9199 6.0000 6.4759 5.9310 0.5758 0.0525 0.1671 21.0098 0.1537 0.1049 0.1094 0.1824 -0.0489 2.8107 0.9225 6.0000 6.4883 5.9754 0.5805 0.0414 0.1638 20.1733 0.1511 0.1026 0.0982 0.1847 -0.0551 2.9378 0.9240 6.0000 6.5020 5.9974 0.5839 0.0299 0.1611 19.4048 0.1488 0.1009 0.0868 0.1863 -0.0621 3.0648 0.9242 6.0000 6.5170 6.0000 0.5857 0.0179 0.1590 18.6970 0.1469 0.0996 0.0751 0.1870 -0.0698 3.1919 0.9228 6.0000 6.5316 6.0001 0.5857 0.0058 0.1569 18.0394 0.1448 0.0979 0.0632 0.1869 -0.0778 3.3190 0.9192 6.0000 6.5456 6.0001 0.5837 -0.0063 0.1549 17.4262 0.1424 0.0959 0.0509 0.1858 -0.0860 3.4460 0.9132 6.0000 6.5590 6.0001 0.5796 -0.0185 0.1529 16.8529 0.1396 0.0934 0.0385 0.1836 -0.0943 3.5731 0.9044 6.0000 6.5716 6.0001 0.5731 -0.0307 0.1508 16.3155 0.1364 0.0904 0.0257 0.1804 -0.1027 3.7002 0.8924 6.0000 6.5833 6.0001 0.5640 -0.0429 0.1488 15.8104 0.1328 0.0868 0.0127 0.1760 -0.1111 3.8272 0.8768 6.0000 6.5942 6.0001 0.5522 -0.0550 0.1468 15.3346 0.1287 0.0827 -0.0006 0.1705 -0.1195 3.9543 0.8574 6.0000 6.6040 6.0001 0.5375 -0.0672 0.1447 14.8852 0.1241 0.0780 -0.0141 0.1638 -0.1279 4.0814 0.8336 6.0000 6.6127 6.0000 0.5197 -0.0793 0.1427 14.4596 0.1190 0.0727 -0.0279 0.1559 -0.1362 4.2084 0.8052 6.0000 6.6201 6.0000 0.4985 -0.0913 0.1407 14.0556 0.1133 0.0669 -0.0420 0.1467 -0.1444 4.3355 0.7717 6.0000 6.6259 6.0000 0.4738 -0.1033 0.1386 13.6709 0.1070 0.0606 -0.0563 0.1362 -0.1525 4.4626 0.7329 6.0000 6.6299 6.0000 0.4454 -0.1152 0.1366 13.3033 0.1001 0.0539 -0.0709 0.1244 -0.1604 4.5897 0.6882 6.0000 6.6316 6.0000 0.4131 -0.1270 0.1346 12.9508 0.0926 0.0469 -0.0857 0.1112 -0.1682 4.7167 0.6375 6.0000 6.6303 6.0000 0.3767 -0.1388 0.1325 12.6109 0.0845 0.0397 -0.1009 0.0966 -0.1758 4.8438 0.5802 6.0000 6.6396 5.9866 0.3360 -0.1501 0.1305 12.3068 0.0757 0.0324 -0.1162 0.0805 -0.1832 4.9709 0.5163 6.0000 6.7094 5.9398 0.2908 -0.1604 0.1285 12.1240 0.0663 0.0253 -0.1316 0.0629 -0.1905 5.0979 0.4453 5.9655 6.8314 5.8522 0.2409 -0.1698 0.1264 12.0392 0.0563 0.0186 -0.1468 0.0438 -0.1973 5.2198 0.3701 5.8260 6.9389 5.6835 0.1885 -0.1786 0.1245 11.9459 0.0461 0.0127 -0.1612 0.0240 -0.2031 5.2528 0.3485 5.7700 6.9662 5.6266 0.1735 -0.1810 0.1240 11.9185 0.0432 0.0112 -0.1651 0.0184 -0.2046 5.2806 0.3299 5.7166 6.9946 5.5744 0.1606 -0.1830 0.1235 11.9045 0.0407 0.0100 -0.1683 0.0136 -0.2058 5.3083 0.3109 5.6578 7.0161 5.5208 0.1475 -0.1851 0.1231 11.8794 0.0383 0.0089 -0.1717 0.0087 -0.2070 5.3361 0.2914 5.5933 7.0356 5.4651 0.1341 -0.1873 0.1226 11.8512 0.0357 0.0078 -0.1751 0.0038 -0.2082 5.3639 0.2716 5.5233 7.0522 5.4074 0.1205 -0.1895 0.1222 11.8185 0.0332 0.0067 -0.1785 -0.0013 -0.2094 5.3917 0.2493 5.4478 7.0645 5.3481 0.1047 -0.1923 0.1217 11.7794 0.0304 0.0057 -0.1824 -0.0074 -0.2109 5.4194 0.2200 5.3666 7.0708 5.3121 0.0822 -0.1964 0.1213 11.7308 0.0267 0.0044 -0.1881 -0.0171 -0.2132 5.4472 0.1796 5.2800 7.0677 5.3533 0.0489 -0.2029 0.1208 11.6677 0.0217 0.0030 -0.1963 -0.0327 -0.2169 5.4750 0.1097 5.1878 7.0503 5.8110 -0.0131 -0.2153 0.1204 11.5823 0.0132 0.0011 -0.2113 -0.0638 -0.2241 5.5000 0.0083 5.1000 5.1001 5.1000 -0.1064 -0.2344 0.1200 8.3952 0.0010 0.0000 -0.2344 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) = 0.095474 TOTAL WEIGHT (Kg) = 0.043299 TOTAL VOLUME (IN**3) = 1.555389 TOTAL PROJECTED AREA (IN**2) = 8.4515 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001098 MOMENT OF INERTIA (Kg-M**2) = 0.000124 STATIC MOMENT, ONE SIDE (IN-LB) = 0.077884 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 = 90.324 INNER LIMIT (NORMALIZED BY RADIUS) = 0.091 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 21155.08 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.