12x4.5MR (12x45MR.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 -7.5178 0.0000 0.0000 0.3250 0.0000 0.5062 0.0000 0.3290 0.0000 0.1450 0.0000 0.0000 0.0960 0.6401 -5.8926 0.0066 -0.2350 0.3221 0.0083 0.4539 0.6257 0.2905 0.1476 0.1498 0.0025 0.0114 0.1920 0.6308 -4.3853 0.0510 -0.4452 0.3228 0.0309 0.4062 2.4223 0.2562 0.1459 0.1630 0.0080 0.0238 0.2880 0.6248 -2.9961 0.1674 -0.5692 0.3267 0.0645 0.3629 5.2867 0.2268 0.1415 0.1826 0.0165 0.0426 0.3840 0.6249 -1.7250 0.3834 -0.5173 0.3333 0.1059 0.3238 9.0280 0.2024 0.1322 0.2068 0.0271 0.0664 0.4800 0.6337 -0.5718 0.7134 -0.2419 0.3423 0.1518 0.2887 13.3078 0.1830 0.1200 0.2337 0.0388 0.0931 0.5760 0.6532 0.4633 1.1561 0.2666 0.3532 0.1990 0.2574 17.7150 0.1681 0.1068 0.2618 0.0507 0.1206 0.6720 0.6843 1.3804 1.6915 0.9738 0.3656 0.2445 0.2296 21.8321 0.1571 0.0941 0.2895 0.0620 0.1468 0.7680 0.7269 2.1795 2.2824 1.7535 0.3791 0.2851 0.2051 25.3134 0.1491 0.0833 0.3152 0.0719 0.1698 0.8640 0.7802 2.8606 2.8782 2.5029 0.3934 0.3176 0.1837 27.9317 0.1433 0.0760 0.3373 0.0788 0.1869 0.9600 0.8430 3.4237 3.4237 3.1405 0.4078 0.3389 0.1652 29.5795 0.1392 0.0745 0.3535 0.0793 0.1937 1.0593 0.9113 3.8821 3.8821 3.6464 0.4223 0.3510 0.1488 30.2524 0.1356 0.0771 0.3641 0.0728 0.1927 1.2161 1.0070 4.3484 4.3484 4.1847 0.4427 0.3621 0.1282 29.6431 0.1291 0.0802 0.3751 0.0582 0.1940 1.3763 1.0899 4.5000 4.5000 4.3856 0.4604 0.3645 0.1128 27.4919 0.1229 0.0827 0.3792 0.0406 0.1996 1.5364 1.1576 4.5000 4.5000 4.4195 0.4750 0.3588 0.1021 24.9925 0.1182 0.0849 0.3763 0.0236 0.2039 1.6966 1.2104 4.5000 4.5000 4.4411 0.4868 0.3500 0.0952 22.8870 0.1152 0.0869 0.3703 0.0097 0.2055 1.8567 1.2484 4.5000 4.5000 4.4530 0.4957 0.3400 0.0909 21.0936 0.1135 0.0887 0.3632 -0.0008 0.2063 2.0168 1.2717 4.5000 4.5000 4.4578 0.5018 0.3290 0.0884 19.5505 0.1124 0.0896 0.3552 -0.0074 0.2064 2.1770 1.2803 4.5000 4.5000 4.4609 0.5053 0.3173 0.0865 18.2106 0.1107 0.0891 0.3463 -0.0102 0.2058 2.3371 1.2745 4.5000 4.5000 4.4644 0.5062 0.3053 0.0848 17.0375 0.1080 0.0867 0.3365 -0.0095 0.2046 2.4972 1.2615 4.5000 4.5000 4.4680 0.5046 0.2928 0.0832 16.0026 0.1050 0.0837 0.3259 -0.0081 0.2022 2.6574 1.2452 4.5000 4.5000 4.4710 0.5005 0.2799 0.0819 15.0835 0.1020 0.0804 0.3146 -0.0074 0.1984 2.8175 1.2257 4.5000 4.5000 4.4734 0.4942 0.2665 0.0807 14.2622 0.0989 0.0769 0.3026 -0.0074 0.1933 2.9777 1.2032 4.5000 4.5000 4.4751 0.4856 0.2528 0.0797 13.5241 0.0958 0.0734 0.2900 -0.0082 0.1871 3.1378 1.1778 4.5000 4.5000 4.4769 0.4749 0.2387 0.0788 12.8574 0.0928 0.0697 0.2768 -0.0098 0.1798 3.2979 1.1495 4.5000 4.5000 4.4786 0.4622 0.2244 0.0780 12.2524 0.0897 0.0659 0.2632 -0.0121 0.1717 3.4581 1.1186 4.5000 4.5000 4.4803 0.4474 0.2098 0.0774 11.7010 0.0866 0.0621 0.2490 -0.0152 0.1629 3.6182 1.0850 4.5000 4.5000 4.4776 0.4308 0.1950 0.0769 11.1965 0.0835 0.0585 0.2345 -0.0202 0.1528 3.7783 1.0490 4.5000 4.5000 4.4681 0.4125 0.1801 0.0766 10.7333 0.0803 0.0553 0.2196 -0.0271 0.1418 3.9385 1.0106 4.5000 4.5000 4.4516 0.3924 0.1651 0.0763 10.3064 0.0771 0.0524 0.2044 -0.0355 0.1299 4.0986 0.9699 4.5000 4.5000 4.4284 0.3707 0.1500 0.0761 9.9118 0.0738 0.0495 0.1890 -0.0450 0.1175 4.2588 0.9271 4.5000 4.5000 4.3993 0.3475 0.1351 0.0760 9.5461 0.0705 0.0467 0.1734 -0.0551 0.1047 4.4189 0.8822 4.5000 4.5000 4.3656 0.3228 0.1202 0.0760 9.2062 0.0671 0.0437 0.1577 -0.0653 0.0918 4.5790 0.8355 4.5000 4.5000 4.3288 0.2968 0.1055 0.0761 8.8895 0.0636 0.0405 0.1420 -0.0753 0.0790 4.7392 0.7869 4.5000 4.5000 4.2915 0.2695 0.0910 0.0762 8.5937 0.0600 0.0371 0.1262 -0.0848 0.0664 4.8993 0.7366 4.5000 4.5000 4.2564 0.2411 0.0768 0.0764 8.3168 0.0563 0.0335 0.1105 -0.0939 0.0541 5.0594 0.6847 4.5000 4.5000 4.2263 0.2116 0.0629 0.0766 8.0571 0.0525 0.0297 0.0950 -0.1025 0.0422 5.2196 0.6313 4.5000 4.5000 4.2046 0.1811 0.0494 0.0769 7.8130 0.0485 0.0257 0.0795 -0.1106 0.0308 5.3797 0.5766 4.5000 4.5000 4.1944 0.1497 0.0364 0.0771 7.5831 0.0445 0.0218 0.0643 -0.1183 0.0199 5.5399 0.5206 4.5000 4.5000 4.1963 0.1175 0.0238 0.0774 7.3664 0.0403 0.0180 0.0493 -0.1257 0.0094 5.6932 0.4658 4.5000 4.5000 4.1475 0.0858 0.0122 0.0777 7.1700 0.0362 0.0145 0.0337 -0.1328 -0.0018 5.7303 0.4493 4.5000 4.5000 4.1208 0.0750 0.0091 0.0778 7.1241 0.0350 0.0136 0.0292 -0.1361 -0.0051 5.7606 0.4325 4.5000 4.5000 4.0952 0.0629 0.0062 0.0779 7.0870 0.0337 0.0126 0.0250 -0.1406 -0.0080 5.7909 0.4123 4.5000 4.5000 4.0719 0.0474 0.0028 0.0779 7.0503 0.0321 0.0115 0.0202 -0.1469 -0.0113 5.8212 0.3883 4.5000 4.5000 4.0486 0.0281 -0.0009 0.0780 7.0140 0.0303 0.0102 0.0148 -0.1552 -0.0149 5.8515 0.3595 4.5000 4.5000 4.0270 0.0042 -0.0052 0.0780 6.9780 0.0281 0.0088 0.0088 -0.1660 -0.0189 5.8818 0.3247 4.5000 4.5000 4.0124 -0.0258 -0.0101 0.0781 6.9424 0.0254 0.0072 0.0019 -0.1800 -0.0233 5.9121 0.2812 4.5000 4.5000 4.0183 -0.0643 -0.0161 0.0782 6.9072 0.0220 0.0054 -0.0062 -0.1986 -0.0282 5.9424 0.2226 4.5000 4.5000 4.0910 -0.1179 -0.0238 0.0782 6.8723 0.0174 0.0034 -0.0164 -0.2251 -0.0340 5.9727 0.1244 4.5000 4.5000 4.5928 -0.2108 -0.0361 0.0783 6.8378 0.0097 0.0011 -0.0322 -0.2726 -0.0424 6.0000 0.0177 4.5000 4.5023 4.5023 -0.3125 -0.0492 0.0783 6.8104 0.0014 0.0000 -0.0492 0.0000 0.0000 RADIUS: 6.00 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.96 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.049358 TOTAL WEIGHT (Kg) = 0.022385 TOTAL VOLUME (IN**3) = 0.804113 TOTAL PROJECTED AREA (IN**2) = 10.5762 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000908 MOMENT OF INERTIA (Kg-M**2) = 0.000103 STATIC MOMENT, ONE SIDE (IN-LB) = 0.054033 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 = 95.147 INNER LIMIT (NORMALIZED BY RADIUS) = 0.054 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 7677.56 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 3.42, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.58, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412