24x12E (24x12E.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 1.3750 12.0000 0.0000 0.0000 0.6875 0.0000 0.3600 0.0000 0.4950 0.0000 0.2450 0.0000 0.0000 0.3120 1.2956 12.0000 0.0441 -0.7203 0.6776 0.0227 0.3559 1.2891 0.4611 0.5505 0.2609 0.0300 0.0063 0.6240 1.2468 12.0000 0.3398 -1.2160 0.6778 0.0832 0.3434 4.9530 0.4282 0.5277 0.3010 0.0587 0.0328 0.9360 1.2340 12.0000 1.0777 -1.1117 0.6864 0.1713 0.3227 10.3842 0.3982 0.4986 0.3589 0.0852 0.0738 1.2480 1.2610 12.0000 2.3394 -0.1871 0.7017 0.2772 0.2937 16.6121 0.3703 0.4665 0.4294 0.1086 0.1253 1.5600 1.3255 12.0000 4.0752 1.5709 0.7218 0.3907 0.2602 22.5759 0.3449 0.4331 0.5069 0.1286 0.1834 1.8720 1.4188 12.0000 6.1163 3.9724 0.7452 0.5020 0.2307 27.4743 0.3273 0.3997 0.5850 0.1447 0.2440 2.1840 1.5279 12.0000 8.2122 6.5399 0.7700 0.6012 0.2050 30.8983 0.3133 0.3673 0.6569 0.1566 0.3026 2.4960 1.6390 12.0000 10.0766 8.8063 0.7945 0.6781 0.1830 32.7218 0.3000 0.3378 0.7146 0.1634 0.3534 2.8080 1.7400 12.0000 11.4246 10.4864 0.8170 0.7230 0.1644 32.9245 0.2860 0.3143 0.7491 0.1629 0.3892 3.1200 1.8219 12.0000 11.9949 11.2958 0.8356 0.7257 0.1488 31.4613 0.2711 0.3013 0.7498 0.1497 0.4000 3.4301 1.8838 12.0000 12.0000 11.4415 0.8491 0.6991 0.1361 29.1091 0.2564 0.2975 0.7267 0.1256 0.3905 3.7068 1.9268 12.0000 12.0000 11.5434 0.8568 0.6746 0.1269 27.2592 0.2445 0.2947 0.7059 0.1038 0.3805 3.9815 1.9588 12.0000 12.0000 11.6218 0.8606 0.6499 0.1195 25.6262 0.2341 0.2928 0.6852 0.0822 0.3693 4.2563 1.9806 12.0000 12.0000 11.6772 0.8607 0.6248 0.1137 24.1665 0.2252 0.2918 0.6646 0.0607 0.3569 4.5310 1.9927 12.0000 12.0000 11.7089 0.8574 0.5995 0.1093 22.8557 0.2177 0.2917 0.6439 0.0396 0.3436 4.8058 1.9957 12.0000 12.0000 11.7152 0.8508 0.5742 0.1060 21.6733 0.2116 0.2920 0.6232 0.0193 0.3299 5.0806 1.9902 12.0000 12.0000 11.6915 0.8410 0.5490 0.1038 20.6020 0.2066 0.2923 0.6026 0.0002 0.3161 5.3553 1.9766 12.0000 12.0000 11.6501 0.8282 0.5241 0.1024 19.6277 0.2023 0.2920 0.5820 -0.0175 0.3026 5.6301 1.9555 12.0000 12.0000 11.6001 0.8126 0.4998 0.1016 18.7382 0.1986 0.2902 0.5614 -0.0332 0.2896 5.9048 1.9275 12.0000 12.0000 11.5445 0.7944 0.4761 0.1012 17.9233 0.1950 0.2864 0.5407 -0.0470 0.2775 6.1796 1.8930 12.0000 12.0000 11.4909 0.7737 0.4531 0.1011 17.1743 0.1913 0.2800 0.5201 -0.0588 0.2663 6.4543 1.8526 12.0000 12.0000 11.4431 0.7507 0.4310 0.1010 16.4836 0.1871 0.2708 0.4994 -0.0687 0.2562 6.7291 1.8069 12.0000 12.0000 11.4044 0.7256 0.4098 0.1009 15.8450 0.1824 0.2588 0.4787 -0.0768 0.2471 7.0039 1.7564 12.0000 12.0000 11.3757 0.6985 0.3892 0.1008 15.2529 0.1771 0.2446 0.4581 -0.0833 0.2389 7.2786 1.7016 12.0000 12.0000 11.3502 0.6696 0.3691 0.1008 14.7026 0.1715 0.2295 0.4374 -0.0892 0.2306 7.5534 1.6430 12.0000 12.0000 11.3254 0.6391 0.3493 0.1007 14.1897 0.1655 0.2139 0.4168 -0.0950 0.2220 7.8281 1.5813 12.0000 12.0000 11.3015 0.6071 0.3297 0.1006 13.7108 0.1591 0.1981 0.3961 -0.1005 0.2130 8.1029 1.5169 12.0000 12.0000 11.2785 0.5738 0.3105 0.1006 13.2626 0.1526 0.1823 0.3755 -0.1061 0.2037 8.3777 1.4503 12.0000 12.0000 11.2566 0.5394 0.2914 0.1005 12.8423 0.1458 0.1666 0.3548 -0.1117 0.1940 8.6524 1.3822 12.0000 12.0000 11.2357 0.5040 0.2726 0.1004 12.4474 0.1388 0.1513 0.3342 -0.1174 0.1839 8.9272 1.3130 12.0000 12.0000 11.2160 0.4679 0.2540 0.1004 12.0757 0.1318 0.1366 0.3135 -0.1233 0.1734 9.2019 1.2433 12.0000 12.0000 11.1976 0.4311 0.2356 0.1003 11.7253 0.1247 0.1225 0.2929 -0.1295 0.1625 9.4767 1.1736 12.0000 12.0000 11.1804 0.3939 0.2173 0.1002 11.3943 0.1176 0.1092 0.2722 -0.1360 0.1512 9.7514 1.1044 12.0000 12.0000 11.1644 0.3564 0.1991 0.1002 11.0813 0.1106 0.0968 0.2516 -0.1430 0.1395 10.0262 1.0364 12.0000 12.0000 11.1493 0.3188 0.1809 0.1001 10.7849 0.1037 0.0853 0.2309 -0.1505 0.1273 10.3010 0.9699 12.0000 12.0000 11.1354 0.2813 0.1628 0.1000 10.5037 0.0970 0.0747 0.2103 -0.1587 0.1147 10.5757 0.9057 12.0000 12.0000 11.1222 0.2439 0.1447 0.1000 10.2367 0.0905 0.0652 0.1896 -0.1674 0.1016 10.8505 0.8441 12.0000 12.0000 11.1093 0.2070 0.1266 0.0999 9.9827 0.0844 0.0567 0.1690 -0.1769 0.0880 11.1252 0.7858 12.0000 12.0000 11.0963 0.1706 0.1084 0.0999 9.7410 0.0785 0.0492 0.1483 -0.1872 0.0739 11.3888 0.7334 12.0000 12.0000 11.0828 0.1364 0.0908 0.0999 9.5197 0.0733 0.0429 0.1285 -0.1979 0.0598 11.4606 0.7198 12.0000 12.0000 11.0789 0.1272 0.0860 0.0999 9.4611 0.0719 0.0413 0.1231 -0.2010 0.0559 11.5212 0.7082 12.0000 12.0000 11.0733 0.1192 0.0819 0.1000 9.4123 0.0708 0.0400 0.1185 -0.2038 0.0525 11.5818 0.6910 12.0000 12.0000 11.0402 0.1054 0.0768 0.1000 9.3639 0.0691 0.0381 0.1121 -0.2098 0.0479 11.6424 0.6655 12.0000 12.0000 10.9747 0.0833 0.0703 0.1000 9.3160 0.0665 0.0353 0.1035 -0.2203 0.0418 11.7030 0.6304 12.0000 12.0000 10.8895 0.0515 0.0623 0.1000 9.2686 0.0630 0.0317 0.0925 -0.2364 0.0340 11.7636 0.5832 12.0000 12.0000 10.7740 0.0076 0.0523 0.1000 9.2217 0.0583 0.0272 0.0787 -0.2590 0.0245 11.8242 0.5190 12.0000 12.0000 10.3820 -0.0532 0.0396 0.1000 9.1752 0.0519 0.0216 0.0614 -0.2911 0.0129 11.8848 0.4246 12.0000 12.0000 9.7974 -0.1441 0.0222 0.1000 9.1292 0.0425 0.0145 0.0385 -0.3396 -0.0016 11.9455 0.2392 12.0000 12.0000 10.1150 -0.3251 -0.0095 0.1000 9.0837 0.0239 0.0047 -0.0013 -0.4372 -0.0245 12.0000 0.0314 12.0000 12.0061 12.0060 -0.5286 -0.0441 0.1000 9.0476 0.0031 0.0000 -0.0441 0.0000 0.0000 RADIUS: 12.00 PROPELLER RADIUS (IN) HUBRAD: 0.69 HUB RADIUS (IN) HUBTRA: 3.12 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.373412 TOTAL WEIGHT (Kg) = 0.169348 TOTAL VOLUME (IN**3) = 6.083366 TOTAL PROJECTED AREA (IN**2) = 33.2901 MOMENT OF INERTIA (SNAIL-IN**2) = 0.024950 MOMENT OF INERTIA (Kg-M**2) = 0.002818 STATIC MOMENT, ONE SIDE (IN-LB) = 0.771295 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 = 73.481 INNER LIMIT (NORMALIZED BY RADIUS) = 0.057 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 4558.33 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 3.12, E63 (Transition Start, Airfoil 1) AIRFOIL2: 6.91, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412