11x11 (11x11.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 2.1306 0.0000 0.0000 0.5000 0.0000 0.5200 0.0000 0.5200 0.0000 0.1000 0.0000 0.0000 0.1450 0.9535 3.1106 0.0197 -0.6897 0.4932 0.0084 0.4865 1.2410 0.4639 0.3838 0.1078 0.0118 -0.1212 0.2900 0.9050 4.0332 0.1539 -1.3297 0.4875 0.0309 0.4546 4.8291 0.4114 0.3771 0.1288 0.0320 -0.1134 0.4350 0.8625 4.8985 0.5054 -1.7493 0.4831 0.0637 0.4242 10.4768 0.3659 0.3634 0.1593 0.0545 -0.0991 0.5800 0.8341 5.7065 1.1625 -1.7882 0.4799 0.1032 0.3955 17.6927 0.3299 0.3437 0.1958 0.0782 -0.0800 0.7250 0.8252 6.4570 2.1869 -1.3152 0.4783 0.1458 0.3683 25.6441 0.3039 0.3199 0.2347 0.1022 -0.0580 0.8700 0.8356 7.1502 3.5903 -0.2567 0.4783 0.1880 0.3427 33.2969 0.2864 0.2939 0.2724 0.1254 -0.0351 1.0150 0.8591 7.7861 5.3021 1.3578 0.4800 0.2261 0.3187 39.7398 0.2738 0.2673 0.3054 0.1468 -0.0130 1.1600 0.8857 8.3646 7.1345 3.3415 0.4836 0.2567 0.2963 44.3885 0.2624 0.2414 0.3303 0.1655 0.0064 1.3050 0.9046 8.8858 8.7678 5.3135 0.4892 0.2762 0.2755 46.9180 0.2492 0.2168 0.3434 0.1806 0.0214 1.4500 0.9068 9.3496 9.7837 6.7222 0.4969 0.2810 0.2563 47.0401 0.2324 0.1933 0.3414 0.1915 0.0303 1.5940 0.8980 9.7533 10.2147 7.5034 0.5061 0.2749 0.2387 45.5651 0.2144 0.1717 0.3289 0.1997 0.0339 1.7202 0.8930 10.0607 10.5367 8.1380 0.5148 0.2683 0.2247 44.2713 0.2006 0.1557 0.3174 0.2063 0.0350 1.8453 0.8905 10.3227 10.8091 8.7169 0.5236 0.2607 0.2119 42.9919 0.1887 0.1421 0.3057 0.2122 0.0344 1.9705 0.8899 10.5420 11.0355 9.2383 0.5325 0.2520 0.2003 41.7111 0.1783 0.1306 0.2937 0.2174 0.0324 2.0957 0.8909 10.7185 11.2166 9.6956 0.5413 0.2425 0.1899 40.4255 0.1692 0.1208 0.2813 0.2216 0.0291 2.2209 0.8932 10.8522 11.3533 10.0834 0.5499 0.2320 0.1807 39.1325 0.1614 0.1129 0.2685 0.2244 0.0244 2.3460 0.8964 10.9433 11.4464 10.3970 0.5579 0.2206 0.1727 37.8302 0.1548 0.1066 0.2554 0.2258 0.0185 2.4712 0.9002 10.9915 11.4967 10.6328 0.5653 0.2084 0.1659 36.5175 0.1493 0.1017 0.2419 0.2260 0.0118 2.5964 0.9042 11.0000 11.5081 10.7909 0.5718 0.1954 0.1602 35.2003 0.1448 0.0980 0.2280 0.2253 0.0045 2.7216 0.9080 11.0000 11.5126 10.9005 0.5773 0.1816 0.1557 33.9505 0.1414 0.0952 0.2138 0.2241 -0.0036 2.8467 0.9113 11.0000 11.5195 10.9699 0.5816 0.1671 0.1524 32.7828 0.1389 0.0933 0.1992 0.2227 -0.0124 2.9719 0.9136 11.0000 11.5298 10.9991 0.5845 0.1519 0.1503 31.6937 0.1373 0.0922 0.1842 0.2211 -0.0219 3.0971 0.9147 11.0000 11.5431 11.0001 0.5858 0.1359 0.1490 30.6759 0.1363 0.0915 0.1688 0.2192 -0.0320 3.2222 0.9140 11.0000 11.5563 11.0003 0.5854 0.1197 0.1478 29.7175 0.1351 0.0906 0.1531 0.2164 -0.0424 3.3474 0.9114 11.0000 11.5692 11.0004 0.5830 0.1032 0.1465 28.8136 0.1335 0.0892 0.1369 0.2128 -0.0531 3.4726 0.9063 11.0000 11.5817 11.0005 0.5784 0.0864 0.1453 27.9599 0.1317 0.0875 0.1204 0.2082 -0.0639 3.5978 0.8985 11.0000 11.5938 11.0005 0.5715 0.0694 0.1440 27.1524 0.1294 0.0852 0.1035 0.2026 -0.0748 3.7229 0.8874 11.0000 11.6054 11.0004 0.5621 0.0522 0.1428 26.3875 0.1267 0.0824 0.0863 0.1960 -0.0858 3.8481 0.8728 11.0000 11.6164 11.0004 0.5500 0.0348 0.1415 25.6618 0.1235 0.0790 0.0686 0.1883 -0.0968 3.9733 0.8542 11.0000 11.6267 11.0004 0.5351 0.0172 0.1403 24.9725 0.1198 0.0750 0.0506 0.1796 -0.1077 4.0984 0.8313 11.0000 11.6361 11.0003 0.5170 -0.0005 0.1390 24.3165 0.1156 0.0704 0.0322 0.1698 -0.1186 4.2236 0.8037 11.0000 11.6444 11.0003 0.4957 -0.0185 0.1378 23.6912 0.1107 0.0653 0.0134 0.1588 -0.1293 4.3488 0.7710 11.0000 11.6514 11.0003 0.4710 -0.0365 0.1365 23.0941 0.1052 0.0596 -0.0057 0.1467 -0.1399 4.4740 0.7328 10.9925 11.6493 10.9927 0.4427 -0.0547 0.1353 22.5095 0.0991 0.0533 -0.0253 0.1333 -0.1503 4.5991 0.6887 10.9459 11.6057 10.9461 0.4105 -0.0731 0.1340 21.8813 0.0923 0.0467 -0.0452 0.1186 -0.1602 4.7243 0.6384 10.8565 11.5162 10.8567 0.3744 -0.0916 0.1328 21.2044 0.0848 0.0398 -0.0656 0.1027 -0.1696 4.8495 0.5816 10.7244 11.3983 10.7077 0.3340 -0.1100 0.1315 20.5098 0.0765 0.0328 -0.0861 0.0854 -0.1787 4.9747 0.5181 10.5496 11.3055 10.4803 0.2893 -0.1273 0.1303 19.8851 0.0675 0.0258 -0.1066 0.0669 -0.1876 5.0998 0.4474 10.3320 11.2647 10.2046 0.2401 -0.1438 0.1290 19.3691 0.0577 0.0191 -0.1268 0.0471 -0.1960 5.2199 0.3724 10.0830 11.2912 9.9238 0.1884 -0.1592 0.1278 18.9970 0.0476 0.0131 -0.1462 0.0269 -0.2037 5.2528 0.3506 10.0081 11.3102 9.8479 0.1735 -0.1635 0.1275 18.9160 0.0447 0.0116 -0.1516 0.0212 -0.2058 5.2806 0.3317 9.9424 11.3296 9.7847 0.1606 -0.1671 0.1272 18.8537 0.0422 0.0103 -0.1561 0.0164 -0.2075 5.3083 0.3123 9.8746 11.3518 9.7229 0.1475 -0.1708 0.1269 18.7961 0.0396 0.0091 -0.1607 0.0114 -0.2092 5.3361 0.2925 9.8047 11.3759 9.6626 0.1341 -0.1746 0.1266 18.7420 0.0370 0.0080 -0.1654 0.0064 -0.2110 5.3639 0.2718 9.7327 11.4009 9.6043 0.1201 -0.1786 0.1264 18.6898 0.0343 0.0069 -0.1703 0.0011 -0.2128 5.3917 0.2488 9.6586 11.4255 9.5485 0.1040 -0.1833 0.1261 18.6375 0.0314 0.0058 -0.1759 -0.0052 -0.2150 5.4194 0.2221 9.5824 11.4471 9.4989 0.0847 -0.1891 0.1258 18.5811 0.0279 0.0046 -0.1828 -0.0132 -0.2178 5.4472 0.1894 9.5041 11.4616 9.5084 0.0597 -0.1969 0.1255 18.5148 0.0238 0.0034 -0.1916 -0.0241 -0.2217 5.4750 0.1435 9.4237 11.4628 9.6647 0.0229 -0.2086 0.1253 18.4290 0.0180 0.0019 -0.2048 -0.0412 -0.2278 5.5000 0.0280 9.3496 9.3496 9.3495 -0.0583 -0.2380 0.1250 15.1390 0.0035 0.0000 -0.2380 0.0000 0.0000 RADIUS: 5.50 PROPELLER RADIUS (IN) HUBRAD: 0.50 HUB RADIUS (IN) HUBTRA: 1.45 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.095738 TOTAL WEIGHT (Kg) = 0.043419 TOTAL VOLUME (IN**3) = 1.559693 TOTAL PROJECTED AREA (IN**2) = 7.5767 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001070 MOMENT OF INERTIA (Kg-M**2) = 0.000121 STATIC MOMENT, ONE SIDE (IN-LB) = 0.076586 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 = 90.337 INNER LIMIT (NORMALIZED BY RADIUS) = 0.091 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 20841.12 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.