9x4.5MR (9x45MR.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 0.6500 -7.5262 0.0000 0.0000 0.3250 0.0000 0.4757 0.0000 0.3092 0.0000 0.0950 0.0000 0.0000 0.0770 0.6377 -5.7921 0.0062 -0.2037 0.3206 0.0070 0.4234 0.7375 0.2700 0.1268 0.0995 0.0007 -0.0169 0.1540 0.6187 -4.1929 0.0486 -0.3910 0.3153 0.0262 0.3760 2.8761 0.2326 0.1259 0.1118 0.0052 -0.0080 0.2310 0.5974 -2.7287 0.1612 -0.5327 0.3099 0.0546 0.3333 6.3370 0.1991 0.1242 0.1300 0.0120 0.0052 0.3080 0.5791 -1.3994 0.3774 -0.5203 0.3048 0.0894 0.2951 11.0354 0.1709 0.1153 0.1509 0.0203 0.0226 0.3850 0.5684 -0.2050 0.7237 -0.2676 0.3008 0.1276 0.2610 16.6548 0.1484 0.1014 0.1737 0.0294 0.0426 0.4620 0.5692 0.8543 1.2112 0.2715 0.2982 0.1668 0.2309 22.6478 0.1314 0.0856 0.1980 0.0381 0.0633 0.5390 0.5833 1.7788 1.8248 1.0860 0.2977 0.2040 0.2046 28.3164 0.1193 0.0705 0.2230 0.0460 0.0830 0.6160 0.6105 2.5683 2.5128 2.0406 0.2997 0.2366 0.1816 32.9933 0.1109 0.0578 0.2473 0.0523 0.0999 0.6930 0.6493 3.2229 3.1875 2.9406 0.3047 0.2619 0.1618 36.2054 0.1051 0.0490 0.2682 0.0562 0.1120 0.7700 0.6979 3.7425 3.7421 3.6215 0.3133 0.2771 0.1450 37.7207 0.1012 0.0459 0.2819 0.0558 0.1158 0.8491 0.7511 4.1360 4.1360 4.0548 0.3241 0.2843 0.1305 37.7829 0.0980 0.0471 0.2891 0.0501 0.1133 0.9652 0.8200 4.4551 4.4551 4.4163 0.3381 0.2898 0.1138 36.3016 0.0933 0.0486 0.2952 0.0373 0.1133 1.0834 0.8788 4.5000 4.5000 4.4848 0.3502 0.2894 0.1016 33.4669 0.0893 0.0499 0.2960 0.0211 0.1177 1.2016 0.9262 4.5000 4.5000 4.4987 0.3601 0.2842 0.0933 30.7960 0.0864 0.0511 0.2921 0.0064 0.1201 1.3198 0.9624 4.5000 4.5000 4.5068 0.3679 0.2777 0.0880 28.4862 0.0847 0.0522 0.2872 -0.0059 0.1222 1.4380 0.9874 4.5000 4.5000 4.5102 0.3737 0.2704 0.0847 26.4751 0.0837 0.0531 0.2814 -0.0151 0.1244 1.5562 1.0013 4.5000 4.5000 4.5110 0.3775 0.2625 0.0827 24.7123 0.0828 0.0534 0.2750 -0.0210 0.1266 1.6744 1.0043 4.5000 4.5000 4.5116 0.3793 0.2540 0.0810 23.1574 0.0813 0.0528 0.2679 -0.0240 0.1285 1.7927 0.9973 4.5000 4.5000 4.5130 0.3794 0.2450 0.0795 21.7776 0.0792 0.0512 0.2601 -0.0244 0.1299 1.9109 0.9866 4.5000 4.5000 4.5146 0.3776 0.2355 0.0781 20.5462 0.0770 0.0494 0.2518 -0.0247 0.1300 2.0291 0.9734 4.5000 4.5000 4.5163 0.3741 0.2256 0.0769 19.4414 0.0748 0.0475 0.2429 -0.0252 0.1290 2.1473 0.9578 4.5000 4.5000 4.5183 0.3689 0.2152 0.0758 18.4455 0.0726 0.0454 0.2336 -0.0260 0.1268 2.2655 0.9398 4.5000 4.5000 4.5202 0.3622 0.2046 0.0749 17.5435 0.0704 0.0433 0.2237 -0.0272 0.1237 2.3837 0.9196 4.5000 4.5000 4.5224 0.3539 0.1936 0.0741 16.7233 0.0681 0.0412 0.2135 -0.0288 0.1197 2.5019 0.8972 4.5000 4.5000 4.5249 0.3441 0.1823 0.0734 15.9744 0.0659 0.0389 0.2029 -0.0307 0.1149 2.6201 0.8728 4.5000 4.5000 4.5272 0.3329 0.1709 0.0729 15.2882 0.0636 0.0367 0.1920 -0.0332 0.1094 2.7383 0.8464 4.5000 4.5000 4.5258 0.3204 0.1591 0.0725 14.6572 0.0613 0.0347 0.1807 -0.0369 0.1028 2.8565 0.8181 4.5000 4.5000 4.5197 0.3065 0.1471 0.0721 14.0753 0.0590 0.0328 0.1692 -0.0420 0.0952 2.9747 0.7880 4.5000 4.5000 4.5088 0.2915 0.1350 0.0719 13.5369 0.0566 0.0311 0.1575 -0.0479 0.0868 3.0929 0.7561 4.5000 4.5000 4.4936 0.2753 0.1228 0.0717 13.0376 0.0542 0.0295 0.1457 -0.0545 0.0779 3.2111 0.7227 4.5000 4.5000 4.4747 0.2580 0.1107 0.0717 12.5732 0.0518 0.0278 0.1337 -0.0612 0.0687 3.3293 0.6877 4.5000 4.5000 4.4532 0.2396 0.0986 0.0717 12.1403 0.0493 0.0260 0.1216 -0.0680 0.0594 3.4476 0.6513 4.5000 4.5000 4.4303 0.2203 0.0867 0.0717 11.7357 0.0467 0.0241 0.1095 -0.0745 0.0502 3.5658 0.6136 4.5000 4.5000 4.4079 0.2001 0.0750 0.0719 11.3570 0.0441 0.0221 0.0974 -0.0807 0.0412 3.6840 0.5746 4.5000 4.5000 4.3877 0.1791 0.0635 0.0720 11.0016 0.0414 0.0199 0.0853 -0.0864 0.0324 3.8022 0.5344 4.5000 4.5000 4.3717 0.1572 0.0524 0.0722 10.6675 0.0386 0.0176 0.0733 -0.0918 0.0240 3.9204 0.4931 4.5000 4.5000 4.3626 0.1347 0.0416 0.0725 10.3530 0.0357 0.0153 0.0615 -0.0968 0.0160 4.0386 0.4508 4.5000 4.5000 4.3608 0.1114 0.0312 0.0727 10.0562 0.0328 0.0129 0.0497 -0.1015 0.0084 4.1568 0.4076 4.5000 4.5000 4.3429 0.0876 0.0212 0.0730 9.7758 0.0298 0.0107 0.0374 -0.1060 0.0002 4.2700 0.3650 4.5000 4.5000 4.2950 0.0638 0.0119 0.0733 9.5214 0.0267 0.0087 0.0252 -0.1106 -0.0082 4.2977 0.3512 4.5000 4.5000 4.2768 0.0547 0.0091 0.0733 9.4611 0.0258 0.0080 0.0215 -0.1134 -0.0106 4.3205 0.3374 4.5000 4.5000 4.2601 0.0448 0.0065 0.0734 9.4123 0.0248 0.0074 0.0181 -0.1169 -0.0129 4.3432 0.3211 4.5000 4.5000 4.2497 0.0324 0.0035 0.0735 9.3639 0.0236 0.0068 0.0142 -0.1218 -0.0154 4.3659 0.3018 4.5000 4.5000 4.2423 0.0171 0.0000 0.0735 9.3160 0.0222 0.0060 0.0097 -0.1282 -0.0182 4.3886 0.2790 4.5000 4.5000 4.2405 -0.0017 -0.0040 0.0736 9.2686 0.0205 0.0051 0.0047 -0.1365 -0.0213 4.4114 0.2514 4.5000 4.5000 4.2500 -0.0252 -0.0087 0.0736 9.2217 0.0185 0.0042 -0.0012 -0.1471 -0.0248 4.4341 0.2172 4.5000 4.5000 4.2847 -0.0552 -0.0145 0.0737 9.1752 0.0160 0.0031 -0.0082 -0.1613 -0.0288 4.4568 0.1711 4.5000 4.5000 4.3927 -0.0970 -0.0220 0.0737 9.1292 0.0126 0.0020 -0.0173 -0.1815 -0.0338 4.4795 0.0946 4.5000 4.5000 4.9342 -0.1688 -0.0343 0.0738 9.0837 0.0070 0.0006 -0.0318 -0.2173 -0.0413 4.5000 0.0139 4.5000 4.5023 4.5022 -0.2451 -0.0470 0.0738 9.0475 0.0010 0.0000 -0.0470 0.0000 0.0000 RADIUS: 4.50 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.77 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.024630 TOTAL WEIGHT (Kg) = 0.011170 TOTAL VOLUME (IN**3) = 0.401249 TOTAL PROJECTED AREA (IN**2) = 6.1573 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000230 MOMENT OF INERTIA (Kg-M**2) = 0.000026 STATIC MOMENT, ONE SIDE (IN-LB) = 0.018534 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 = 99.555 INNER LIMIT (NORMALIZED BY RADIUS) = 0.072 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 10977.41 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.57, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.18, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412