12x6EP(F2B) (12x6EP(F2B).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 0.8000 6.0000 0.0000 0.0000 0.4000 0.0000 0.3562 0.0000 0.2850 0.0000 0.0250 0.0000 0.0000 0.0950 0.7648 6.0000 0.0114 -0.3913 0.3956 0.0070 0.3548 1.0896 0.2714 0.1858 0.0313 0.0078 -0.1034 0.1900 0.7207 6.0000 0.0899 -0.7703 0.3921 0.0259 0.3506 4.3063 0.2527 0.1851 0.0485 0.0276 -0.0966 0.2850 0.6765 6.0000 0.3028 -1.0524 0.3898 0.0539 0.3436 9.5985 0.2325 0.1806 0.0733 0.0519 -0.0851 0.3800 0.6417 6.0000 0.7176 -1.0655 0.3889 0.0880 0.3338 16.7278 0.2142 0.1665 0.1027 0.0789 -0.0684 0.4750 0.6245 6.0000 1.3905 -0.6651 0.3897 0.1253 0.3212 24.9813 0.2006 0.1477 0.1357 0.1061 -0.0479 0.5700 0.6286 6.0000 2.3396 0.2476 0.3923 0.1632 0.3058 33.1549 0.1922 0.1280 0.1705 0.1310 -0.0252 0.6650 0.6523 6.0000 3.4997 1.6495 0.3971 0.1989 0.2875 39.9493 0.1876 0.1104 0.2044 0.1516 -0.0017 0.7600 0.6893 6.0000 4.6843 3.2580 0.4040 0.2297 0.2665 44.4496 0.1837 0.0966 0.2342 0.1660 0.0206 0.8550 0.7331 6.0000 5.6070 4.5835 0.4135 0.2528 0.2427 46.2258 0.1779 0.0875 0.2570 0.1722 0.0395 0.9500 0.7798 6.0000 5.9967 5.2539 0.4256 0.2654 0.2160 45.1323 0.1685 0.0837 0.2699 0.1681 0.0518 1.0484 0.8281 6.0000 6.0000 5.4407 0.4393 0.2706 0.1855 42.3282 0.1536 0.0818 0.2757 0.1561 0.0587 1.2055 0.8958 6.0000 6.0000 5.7158 0.4582 0.2770 0.1425 38.3839 0.1276 0.0749 0.2831 0.1368 0.0698 1.3660 0.9535 6.0000 6.0000 5.8997 0.4739 0.2810 0.1139 34.9556 0.1086 0.0689 0.2883 0.1179 0.0808 1.5266 1.0000 6.0000 6.0000 5.9703 0.4861 0.2822 0.1009 32.0279 0.1009 0.0675 0.2913 0.1016 0.0913 1.6871 1.0370 6.0000 6.0000 5.9618 0.4949 0.2803 0.1000 29.5111 0.1037 0.0713 0.2921 0.0892 0.1010 1.8476 1.0655 6.0000 6.0000 5.9451 0.5005 0.2761 0.1000 27.3323 0.1066 0.0752 0.2910 0.0777 0.1081 2.0081 1.0859 6.0000 6.0000 5.9249 0.5031 0.2700 0.1000 25.4329 0.1086 0.0786 0.2881 0.0665 0.1126 2.1686 1.0987 6.0000 6.0000 5.9036 0.5028 0.2621 0.1000 23.7658 0.1099 0.0815 0.2833 0.0556 0.1146 2.3291 1.1042 6.0000 6.0000 5.8830 0.4997 0.2526 0.1000 22.2933 0.1104 0.0834 0.2769 0.0449 0.1146 2.4897 1.1032 6.0000 6.0000 5.8628 0.4941 0.2418 0.1000 20.9848 0.1103 0.0845 0.2690 0.0344 0.1127 2.6502 1.0959 6.0000 6.0000 5.8424 0.4860 0.2299 0.1000 19.8155 0.1096 0.0848 0.2597 0.0244 0.1094 2.8107 1.0828 6.0000 6.0000 5.8209 0.4757 0.2171 0.1000 18.7652 0.1083 0.0841 0.2491 0.0149 0.1048 2.9712 1.0645 6.0000 6.0000 5.7971 0.4632 0.2035 0.1000 17.8171 0.1064 0.0826 0.2373 0.0060 0.0991 3.1317 1.0414 6.0000 6.0000 5.7732 0.4488 0.1892 0.1000 16.9576 0.1041 0.0803 0.2244 -0.0022 0.0924 3.2922 1.0140 6.0000 6.0000 5.7489 0.4326 0.1744 0.1000 16.1750 0.1014 0.0772 0.2106 -0.0099 0.0848 3.4528 0.9827 6.0000 6.0000 5.7252 0.4148 0.1591 0.1000 15.4598 0.0983 0.0734 0.1959 -0.0170 0.0765 3.6133 0.9480 6.0000 6.0000 5.7027 0.3955 0.1435 0.1000 14.8039 0.0948 0.0691 0.1805 -0.0237 0.0677 3.7738 0.9105 6.0000 6.0000 5.6815 0.3749 0.1277 0.1000 14.2002 0.0911 0.0644 0.1645 -0.0299 0.0583 3.9343 0.8705 6.0000 6.0000 5.6626 0.3531 0.1117 0.1000 13.6429 0.0871 0.0593 0.1481 -0.0357 0.0485 4.0948 0.8286 6.0000 6.0000 5.6466 0.3303 0.0956 0.1000 13.1270 0.0829 0.0541 0.1312 -0.0412 0.0383 4.2553 0.7852 6.0000 6.0000 5.6343 0.3066 0.0795 0.1000 12.6480 0.0785 0.0487 0.1141 -0.0466 0.0278 4.4159 0.7408 6.0000 6.0000 5.6259 0.2823 0.0635 0.1000 12.2023 0.0741 0.0435 0.0968 -0.0519 0.0171 4.5764 0.6958 6.0000 6.0000 5.6202 0.2574 0.0476 0.1000 11.7865 0.0696 0.0384 0.0795 -0.0573 0.0061 4.7369 0.6508 6.0000 6.0000 5.6163 0.2321 0.0318 0.1000 11.3977 0.0651 0.0337 0.0622 -0.0630 -0.0051 4.8974 0.6062 6.0000 6.0000 5.6146 0.2066 0.0164 0.1000 11.0335 0.0606 0.0293 0.0452 -0.0691 -0.0165 5.0579 0.5625 6.0000 6.0000 5.6152 0.1810 0.0013 0.1000 10.6915 0.0563 0.0253 0.0285 -0.0755 -0.0278 5.2184 0.5202 6.0000 6.0000 5.6186 0.1556 -0.0134 0.1000 10.3699 0.0520 0.0217 0.0122 -0.0824 -0.0391 5.3790 0.4796 6.0000 6.0000 5.6127 0.1303 -0.0275 0.1000 10.0669 0.0480 0.0185 -0.0038 -0.0898 -0.0505 5.5395 0.4414 6.0000 6.0000 5.5699 0.1055 -0.0410 0.1000 9.7809 0.0441 0.0158 -0.0199 -0.0978 -0.0624 5.6932 0.4074 6.0000 6.0000 5.4829 0.0822 -0.0533 0.1000 9.5217 0.0407 0.0135 -0.0350 -0.1060 -0.0740 5.7303 0.3996 6.0000 6.0000 5.4533 0.0766 -0.0562 0.1000 9.4611 0.0400 0.0130 -0.0386 -0.1082 -0.0768 5.7606 0.3909 6.0000 6.0000 5.4261 0.0698 -0.0589 0.1000 9.4123 0.0391 0.0124 -0.0420 -0.1112 -0.0793 5.7909 0.3787 6.0000 6.0000 5.3336 0.0592 -0.0622 0.1000 9.3639 0.0379 0.0117 -0.0462 -0.1161 -0.0823 5.8212 0.3624 6.0000 6.0000 5.2457 0.0446 -0.0661 0.1000 9.3160 0.0362 0.0107 -0.0511 -0.1234 -0.0856 5.8515 0.3412 6.0000 6.0000 5.1688 0.0251 -0.0708 0.1000 9.2686 0.0341 0.0095 -0.0570 -0.1334 -0.0895 5.8818 0.3137 6.0000 6.0000 5.1103 -0.0007 -0.0764 0.1000 9.2217 0.0314 0.0081 -0.0640 -0.1468 -0.0940 5.9121 0.2771 6.0000 6.0000 5.0940 -0.0358 -0.0835 0.1000 9.1752 0.0277 0.0063 -0.0728 -0.1652 -0.0994 5.9424 0.2231 6.0000 6.0000 5.2063 -0.0880 -0.0932 0.1000 9.1292 0.0223 0.0041 -0.0849 -0.1930 -0.1064 5.9727 0.1213 6.0000 6.0000 6.0315 -0.1876 -0.1105 0.1000 9.0837 0.0121 0.0013 -0.1061 -0.2463 -0.1181 6.0000 0.0174 6.0000 6.0030 6.0030 -0.2894 -0.1276 0.1000 9.0476 0.0017 0.0000 -0.1276 0.0000 0.0000 RADIUS: 6.00 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 0.95 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.052028 TOTAL WEIGHT (Kg) = 0.023595 TOTAL VOLUME (IN**3) = 0.847595 TOTAL PROJECTED AREA (IN**2) = 8.9881 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000917 MOMENT OF INERTIA (Kg-M**2) = 0.000104 STATIC MOMENT, ONE SIDE (IN-LB) = 0.054876 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 = 81.445 INNER LIMIT (NORMALIZED BY RADIUS) = 0.067 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 7880.79 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.95, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.39, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412