9x4M-LH (9x4M-LH.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 1.2400 0.6952 0.0000 0.0000 0.6200 0.0000 0.2888 0.0000 0.3581 0.0000 0.2200 0.0000 0.0000 0.0700 1.2408 0.9472 0.0390 -0.2260 0.6199 0.0507 0.2826 5.0715 0.3506 0.6160 0.2188 -0.0010 -0.0735 0.1400 1.2405 1.1893 0.1467 -0.3769 0.6196 0.0867 0.2766 9.4675 0.3431 0.6055 0.2156 0.0068 -0.0776 0.2100 1.2357 1.4213 0.3110 -0.4610 0.6194 0.1102 0.2707 13.2634 0.3345 0.5890 0.2107 0.0203 -0.0835 0.2800 1.2232 1.6434 0.5232 -0.4512 0.6193 0.1234 0.2650 16.5622 0.3241 0.5515 0.2038 0.0403 -0.0897 0.3500 1.1999 1.8555 0.7777 -0.3475 0.6195 0.1284 0.2593 19.4760 0.3112 0.4921 0.1960 0.0673 -0.0956 0.4200 1.1619 2.0575 1.0740 -0.1428 0.6201 0.1273 0.2539 22.1452 0.2950 0.4191 0.1886 0.1019 -0.1001 0.4900 1.1029 2.2496 1.4231 0.1588 0.6212 0.1222 0.2485 24.8085 0.2741 0.3402 0.1820 0.1458 -0.1018 0.5600 1.0080 2.4316 1.8786 0.5943 0.6231 0.1151 0.2433 28.0985 0.2453 0.2604 0.1759 0.2044 -0.0972 0.6300 0.9047 2.6037 2.4371 1.2056 0.6257 0.1081 0.2383 31.6194 0.2156 0.1964 0.1706 0.2633 -0.0856 0.7000 0.8423 2.7658 2.8828 1.7493 0.6293 0.1034 0.2333 33.2425 0.1965 0.1627 0.1661 0.2972 -0.0735 0.7726 0.8229 2.9234 3.0938 1.9714 0.6336 0.1007 0.2284 32.5095 0.1879 0.1507 0.1620 0.3067 -0.0657 0.8902 0.8081 3.1557 3.3445 2.2346 0.6406 0.0961 0.2206 30.8768 0.1783 0.1369 0.1553 0.3153 -0.0573 1.0104 0.7966 3.3641 3.5701 2.4915 0.6476 0.0910 0.2131 29.3509 0.1698 0.1254 0.1483 0.3230 -0.0509 1.1306 0.7886 3.5430 3.7650 2.7324 0.6540 0.0855 0.2060 27.9230 0.1625 0.1160 0.1411 0.3293 -0.0465 1.2508 0.7836 3.6924 3.9293 2.9533 0.6598 0.0794 0.1993 26.5631 0.1562 0.1082 0.1338 0.3341 -0.0436 1.3710 0.7812 3.8123 4.0632 3.1511 0.6646 0.0729 0.1930 25.2517 0.1508 0.1018 0.1263 0.3371 -0.0420 1.4912 0.7809 3.9028 4.1668 3.3226 0.6682 0.0659 0.1871 23.9752 0.1461 0.0965 0.1186 0.3383 -0.0415 1.6114 0.7823 3.9637 4.2404 3.4652 0.6705 0.0584 0.1816 22.7242 0.1421 0.0921 0.1107 0.3376 -0.0418 1.7317 0.7850 3.9952 4.2841 3.5765 0.6710 0.0505 0.1765 21.4918 0.1385 0.0883 0.1026 0.3348 -0.0429 1.8519 0.7885 4.0000 4.3007 3.6569 0.6697 0.0421 0.1718 20.2851 0.1354 0.0852 0.0943 0.3300 -0.0447 1.9721 0.7924 4.0000 4.3125 3.7254 0.6663 0.0335 0.1675 19.1898 0.1327 0.0826 0.0858 0.3232 -0.0474 2.0923 0.7963 4.0000 4.3243 3.7862 0.6605 0.0246 0.1636 18.2081 0.1302 0.0803 0.0771 0.3144 -0.0509 2.2125 0.7996 4.0000 4.3362 3.8393 0.6521 0.0155 0.1601 17.3241 0.1280 0.0783 0.0681 0.3034 -0.0552 2.3327 0.8021 4.0000 4.3484 3.8848 0.6409 0.0062 0.1570 16.5247 0.1259 0.0765 0.0589 0.2902 -0.0601 2.4529 0.8031 4.0000 4.3609 3.9227 0.6267 -0.0033 0.1543 15.7990 0.1239 0.0748 0.0495 0.2747 -0.0655 2.5731 0.8023 4.0000 4.3738 3.9530 0.6091 -0.0131 0.1520 15.1381 0.1219 0.0730 0.0398 0.2569 -0.0714 2.6933 0.7992 4.0000 4.3872 3.9758 0.5880 -0.0231 0.1501 14.5341 0.1200 0.0712 0.0299 0.2366 -0.0778 2.8135 0.7934 4.0000 4.4007 3.9911 0.5632 -0.0332 0.1484 13.9791 0.1178 0.0692 0.0197 0.2138 -0.0844 2.9337 0.7845 4.0000 4.4137 3.9989 0.5343 -0.0432 0.1468 13.4656 0.1151 0.0668 0.0093 0.1886 -0.0911 3.0539 0.7719 4.0000 4.4260 4.0000 0.5012 -0.0532 0.1451 12.9887 0.1120 0.0639 -0.0014 0.1607 -0.0979 3.1741 0.7553 4.0000 4.4376 4.0001 0.4636 -0.0632 0.1434 12.5442 0.1083 0.0605 -0.0123 0.1301 -0.1047 3.2943 0.7342 4.0000 4.4482 4.0001 0.4214 -0.0730 0.1417 12.1284 0.1041 0.0565 -0.0236 0.0969 -0.1115 3.4146 0.7082 4.0000 4.4578 4.0001 0.3741 -0.0828 0.1401 11.7380 0.0992 0.0520 -0.0351 0.0609 -0.1181 3.5348 0.6768 4.0000 4.4660 4.0001 0.3217 -0.0924 0.1384 11.3698 0.0937 0.0469 -0.0469 0.0221 -0.1247 3.6550 0.6395 4.0000 4.4726 4.0000 0.2639 -0.1019 0.1367 11.0210 0.0874 0.0414 -0.0590 -0.0195 -0.1311 3.7752 0.5960 4.0000 4.4789 3.9969 0.2005 -0.1112 0.1351 10.6929 0.0805 0.0356 -0.0715 -0.0640 -0.1373 3.8954 0.5459 3.9946 4.5062 3.9581 0.1311 -0.1198 0.1334 10.4320 0.0728 0.0295 -0.0842 -0.1115 -0.1436 4.0156 0.4888 3.9602 4.5582 3.8728 0.0556 -0.1273 0.1317 10.2406 0.0644 0.0234 -0.0970 -0.1619 -0.1494 4.1358 0.4242 3.8940 4.6545 3.7625 -0.0262 -0.1340 0.1301 10.1550 0.0552 0.0174 -0.1095 -0.2154 -0.1547 4.2509 0.3548 3.8010 4.8094 3.6555 -0.1108 -0.1399 0.1285 10.2076 0.0456 0.0120 -0.1214 -0.2695 -0.1592 4.2786 0.3369 3.7743 4.8555 3.6326 -0.1320 -0.1414 0.1281 10.2381 0.0432 0.0108 -0.1243 -0.2829 -0.1603 4.3013 0.3220 3.7512 4.8958 3.6150 -0.1497 -0.1426 0.1278 10.2680 0.0411 0.0099 -0.1267 -0.2940 -0.1611 4.3239 0.3068 3.7270 4.9382 3.5987 -0.1676 -0.1438 0.1274 10.3020 0.0391 0.0090 -0.1290 -0.3052 -0.1619 4.3465 0.2912 3.7017 4.9827 3.5837 -0.1857 -0.1451 0.1271 10.3398 0.0370 0.0081 -0.1314 -0.3165 -0.1628 4.3691 0.2750 3.6752 5.0287 3.5703 -0.2044 -0.1465 0.1268 10.3804 0.0349 0.0072 -0.1339 -0.3281 -0.1636 4.3918 0.2579 3.6476 5.0757 3.5586 -0.2245 -0.1481 0.1265 10.4225 0.0326 0.0063 -0.1367 -0.3406 -0.1647 4.4144 0.2375 3.6189 5.1234 3.5538 -0.2471 -0.1503 0.1262 10.4656 0.0300 0.0053 -0.1401 -0.3543 -0.1659 4.4370 0.2093 3.5891 5.1706 3.5843 -0.2743 -0.1535 0.1259 10.5072 0.0263 0.0042 -0.1448 -0.3691 -0.1677 4.4596 0.1624 3.5582 5.2156 3.7244 -0.3115 -0.1591 0.1256 10.5441 0.0204 0.0025 -0.1526 -0.3856 -0.1705 4.4800 0.0409 3.5294 3.5294 3.5294 -0.3858 -0.1765 0.1253 7.1467 0.0051 0.0000 -0.1765 0.0000 0.0000 RADIUS: 4.50 PROPELLER RADIUS (IN) HUBRAD: 0.62 HUB RADIUS (IN) HUBTRA: 0.70 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.071074 TOTAL WEIGHT (Kg) = 0.032233 TOTAL VOLUME (IN**3) = 1.157894 TOTAL PROJECTED AREA (IN**2) = 6.5144 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000449 MOMENT OF INERTIA (Kg-M**2) = 0.000051 STATIC MOMENT, ONE SIDE (IN-LB) = 0.039225 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 = 98.072 INNER LIMIT (NORMALIZED BY RADIUS) = 0.138 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 23132.14 BASED ON MODULUS (MILLION) = 2.60 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.