11.5x6 (115x6.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 1.3532 0.0000 0.0000 0.5000 0.0000 0.3902 0.0000 0.3902 0.0000 0.1250 0.0000 0.0000 0.1400 0.9612 1.8379 0.0149 -0.6147 0.4934 0.0049 0.3722 0.9722 0.3577 0.3846 0.1291 0.0090 -0.1004 0.2800 0.9298 2.2960 0.1140 -1.1665 0.4877 0.0179 0.3548 3.7074 0.3299 0.3793 0.1399 0.0204 -0.0982 0.4200 0.9086 2.7274 0.3623 -1.5124 0.4832 0.0367 0.3382 7.8178 0.3073 0.3682 0.1550 0.0314 -0.0940 0.5600 0.8999 3.1321 0.7994 -1.5437 0.4798 0.0592 0.3224 12.7994 0.2901 0.3518 0.1727 0.0420 -0.0877 0.7000 0.9042 3.5101 1.4333 -1.2067 0.4779 0.0831 0.3072 18.0503 0.2778 0.3317 0.1915 0.0524 -0.0796 0.8400 0.9190 3.8614 2.2373 -0.5094 0.4774 0.1064 0.2928 22.9724 0.2691 0.3092 0.2095 0.0628 -0.0699 0.9800 0.9395 4.1859 3.1477 0.4734 0.4787 0.1269 0.2791 27.0757 0.2622 0.2853 0.2248 0.0732 -0.0591 1.1200 0.9592 4.4838 4.0648 1.6000 0.4817 0.1425 0.2661 30.0113 0.2553 0.2610 0.2353 0.0837 -0.0479 1.2600 0.9712 4.7550 4.8556 2.6650 0.4867 0.1510 0.2539 31.5221 0.2466 0.2371 0.2389 0.0942 -0.0376 1.4000 0.9695 4.9995 5.3579 3.4057 0.4938 0.1502 0.2424 31.3456 0.2350 0.2144 0.2334 0.1043 -0.0299 1.5398 0.9592 5.2169 5.5972 3.8143 0.5026 0.1427 0.2316 30.0514 0.2222 0.1944 0.2214 0.1136 -0.0256 1.6753 0.9523 5.4023 5.7994 4.1866 0.5117 0.1346 0.2219 28.8531 0.2113 0.1781 0.2096 0.1223 -0.0235 1.8105 0.9480 5.5625 5.9745 4.5323 0.5211 0.1259 0.2128 27.7083 0.2017 0.1645 0.1976 0.1306 -0.0233 1.9458 0.9461 5.6977 6.1233 4.8473 0.5308 0.1165 0.2044 26.6043 0.1934 0.1531 0.1854 0.1382 -0.0246 2.0810 0.9461 5.8080 6.2460 5.1274 0.5403 0.1064 0.1967 25.5333 0.1861 0.1435 0.1730 0.1452 -0.0272 2.2163 0.9476 5.8933 6.3431 5.3689 0.5496 0.0957 0.1897 24.4895 0.1798 0.1355 0.1605 0.1514 -0.0310 2.3516 0.9501 5.9538 6.4147 5.5687 0.5582 0.0844 0.1834 23.4683 0.1742 0.1289 0.1478 0.1568 -0.0358 2.4868 0.9534 5.9893 6.4614 5.7243 0.5662 0.0726 0.1777 22.4663 0.1694 0.1234 0.1349 0.1613 -0.0414 2.6221 0.9570 6.0000 6.4834 5.8339 0.5730 0.0602 0.1727 21.4810 0.1653 0.1190 0.1218 0.1648 -0.0477 2.7573 0.9605 6.0000 6.4953 5.9101 0.5787 0.0473 0.1684 20.5518 0.1618 0.1155 0.1085 0.1673 -0.0550 2.8926 0.9635 6.0000 6.5083 5.9630 0.5829 0.0340 0.1648 19.7023 0.1588 0.1128 0.0951 0.1688 -0.0631 3.0278 0.9655 6.0000 6.5226 5.9929 0.5853 0.0203 0.1619 18.9243 0.1563 0.1107 0.0815 0.1693 -0.0720 3.1631 0.9663 6.0000 6.5384 6.0000 0.5858 0.0062 0.1596 18.2104 0.1542 0.1091 0.0676 0.1685 -0.0816 3.2984 0.9653 6.0000 6.5543 6.0000 0.5842 -0.0079 0.1575 17.5502 0.1520 0.1075 0.0536 0.1665 -0.0916 3.4336 0.9621 6.0000 6.5696 6.0001 0.5801 -0.0221 0.1554 16.9362 0.1495 0.1054 0.0395 0.1631 -0.1016 3.5689 0.9565 6.0000 6.5841 6.0001 0.5733 -0.0361 0.1534 16.3634 0.1467 0.1027 0.0251 0.1582 -0.1117 3.7041 0.9478 6.0000 6.5979 6.0001 0.5637 -0.0501 0.1513 15.8276 0.1434 0.0995 0.0105 0.1517 -0.1218 3.8394 0.9358 6.0000 6.6108 6.0001 0.5510 -0.0640 0.1492 15.3250 0.1396 0.0957 -0.0042 0.1437 -0.1318 3.9747 0.9201 6.0000 6.6228 6.0000 0.5349 -0.0777 0.1471 14.8525 0.1354 0.0912 -0.0191 0.1340 -0.1418 4.1099 0.9001 6.0000 6.6336 6.0000 0.5152 -0.0913 0.1451 14.4069 0.1306 0.0861 -0.0342 0.1226 -0.1516 4.2452 0.8756 6.0000 6.6433 6.0000 0.4917 -0.1048 0.1430 13.9857 0.1252 0.0803 -0.0495 0.1094 -0.1612 4.3804 0.8461 6.0000 6.6516 6.0000 0.4642 -0.1181 0.1409 13.5864 0.1192 0.0740 -0.0649 0.0944 -0.1707 4.5157 0.8112 6.0000 6.6584 6.0000 0.4324 -0.1312 0.1389 13.2068 0.1126 0.0670 -0.0806 0.0774 -0.1799 4.6509 0.7704 6.0000 6.6632 6.0000 0.3960 -0.1441 0.1368 12.8446 0.1054 0.0596 -0.0964 0.0585 -0.1888 4.7862 0.7235 6.0000 6.6657 6.0000 0.3549 -0.1569 0.1347 12.4977 0.0975 0.0518 -0.1124 0.0375 -0.1975 4.9215 0.6699 6.0000 6.6651 6.0000 0.3089 -0.1694 0.1327 12.1636 0.0889 0.0438 -0.1286 0.0145 -0.2059 5.0567 0.6092 6.0000 6.6605 6.0000 0.2576 -0.1817 0.1306 11.8395 0.0796 0.0357 -0.1450 -0.0107 -0.2139 5.1920 0.5412 6.0000 6.6498 6.0000 0.2008 -0.1938 0.1285 11.5215 0.0695 0.0278 -0.1616 -0.0381 -0.2217 5.3272 0.4652 6.0000 6.6298 6.0000 0.1384 -0.2057 0.1264 11.2036 0.0588 0.0203 -0.1784 -0.0677 -0.2291 5.4570 0.3846 6.0000 6.5952 6.0000 0.0730 -0.2170 0.1245 10.8881 0.0479 0.0137 -0.1946 -0.0983 -0.2359 5.4915 0.3618 6.0000 6.5819 6.0000 0.0546 -0.2199 0.1239 10.7997 0.0448 0.0121 -0.1990 -0.1068 -0.2376 5.5206 0.3422 6.0000 6.5688 6.0000 0.0388 -0.2224 0.1235 10.7233 0.0423 0.0108 -0.2026 -0.1141 -0.2391 5.5496 0.3222 6.0000 6.5535 6.0000 0.0228 -0.2249 0.1230 10.6442 0.0396 0.0096 -0.2063 -0.1215 -0.2405 5.5787 0.3018 6.0000 6.5355 6.0000 0.0065 -0.2273 0.1226 10.5617 0.0370 0.0084 -0.2100 -0.1290 -0.2420 5.6077 0.2810 6.0000 6.5143 6.0000 -0.0102 -0.2298 0.1221 10.4749 0.0343 0.0073 -0.2137 -0.1366 -0.2434 5.6367 0.2579 6.0000 6.4891 6.0003 -0.0288 -0.2325 0.1217 10.3827 0.0314 0.0061 -0.2178 -0.1452 -0.2450 5.6658 0.2276 6.0000 6.4591 6.0103 -0.0546 -0.2365 0.1213 10.2839 0.0276 0.0048 -0.2236 -0.1577 -0.2475 5.6948 0.1854 6.0000 6.4223 6.0681 -0.0919 -0.2425 0.1208 10.1754 0.0224 0.0032 -0.2319 -0.1765 -0.2515 5.7239 0.1117 6.0000 6.3763 6.3700 -0.1601 -0.2537 0.1204 10.0539 0.0134 0.0012 -0.2474 -0.2120 -0.2593 5.7500 0.0086 6.0000 6.0002 5.9999 -0.2576 -0.2701 0.1200 9.4296 0.0010 0.0000 -0.2701 0.0000 0.0000 RADIUS: 5.75 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) = 0.105907 TOTAL WEIGHT (Kg) = 0.048030 TOTAL VOLUME (IN**3) = 1.725364 TOTAL PROJECTED AREA (IN**2) = 9.2124 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001365 MOMENT OF INERTIA (Kg-M**2) = 0.000154 STATIC MOMENT, ONE SIDE (IN-LB) = 0.092173 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 = 90.237 INNER LIMIT (NORMALIZED BY RADIUS) = 0.087 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 19994.96 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.