15x5.5MR (15x55MR.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 -10.5238 0.0000 0.0000 0.4000 0.0000 0.3812 0.0000 0.3050 0.0000 0.1550 0.0000 0.0000 0.1170 0.7885 -8.4120 0.0066 -0.2684 0.3954 0.0088 0.3781 0.5176 0.2981 0.2019 0.1606 0.0013 0.0077 0.2340 0.7784 -6.4494 0.0518 -0.5053 0.3931 0.0330 0.3685 2.0171 0.2868 0.1994 0.1761 0.0044 0.0224 0.3510 0.7720 -4.6360 0.1715 -0.6338 0.3932 0.0691 0.3525 4.4461 0.2721 0.1919 0.1995 0.0101 0.0447 0.4680 0.7719 -2.9717 0.3949 -0.5761 0.3957 0.1137 0.3301 7.6481 0.2548 0.1793 0.2285 0.0178 0.0724 0.5850 0.7804 -1.4566 0.7398 -0.2874 0.4005 0.1636 0.3013 11.3794 0.2351 0.1638 0.2609 0.0271 0.1032 0.7020 0.7996 -0.0906 1.2101 0.2432 0.4075 0.2154 0.2697 15.3420 0.2156 0.1474 0.2945 0.0375 0.1351 0.8190 0.8305 1.1263 1.7939 0.9889 0.4166 0.2660 0.2414 19.2188 0.2005 0.1318 0.3272 0.0484 0.1656 0.9360 0.8734 2.1939 2.4630 1.8198 0.4278 0.3119 0.2164 22.7238 0.1890 0.1185 0.3569 0.0591 0.1926 1.0530 0.9280 3.1124 3.1758 2.6648 0.4410 0.3499 0.1944 25.6409 0.1804 0.1097 0.3819 0.0677 0.2126 1.1700 0.9932 3.8818 3.8823 3.4548 0.4561 0.3767 0.1752 27.8386 0.1740 0.1075 0.4001 0.0704 0.2207 1.2914 1.0646 4.5224 4.5224 4.1501 0.4724 0.3936 0.1581 29.1333 0.1683 0.1103 0.4128 0.0657 0.2193 1.4883 1.1679 5.2200 5.2200 4.9417 0.4961 0.4095 0.1357 29.1708 0.1585 0.1125 0.4267 0.0541 0.2212 1.6896 1.2575 5.4965 5.4965 5.2903 0.5168 0.4142 0.1189 27.3727 0.1495 0.1144 0.4328 0.0374 0.2278 1.8909 1.3310 5.5000 5.5000 5.3458 0.5340 0.4088 0.1072 24.8404 0.1426 0.1161 0.4306 0.0199 0.2346 2.0922 1.3887 5.5000 5.5000 5.3801 0.5478 0.3988 0.0994 22.7035 0.1380 0.1178 0.4239 0.0056 0.2372 2.2936 1.4305 5.5000 5.5000 5.4001 0.5584 0.3874 0.0946 20.8897 0.1354 0.1195 0.4160 -0.0054 0.2385 2.4949 1.4567 5.5000 5.5000 5.4089 0.5658 0.3748 0.0917 19.3340 0.1336 0.1205 0.4069 -0.0123 0.2386 2.6962 1.4674 5.5000 5.5000 5.4135 0.5701 0.3613 0.0897 17.9868 0.1316 0.1198 0.3968 -0.0154 0.2378 2.8975 1.4628 5.5000 5.5000 5.4186 0.5715 0.3475 0.0879 16.8100 0.1285 0.1169 0.3858 -0.0150 0.2362 3.0988 1.4488 5.5000 5.5000 5.4234 0.5700 0.3332 0.0863 15.7740 0.1250 0.1128 0.3737 -0.0133 0.2333 3.3001 1.4309 5.5000 5.5000 5.4277 0.5657 0.3184 0.0848 14.8556 0.1214 0.1085 0.3609 -0.0124 0.2287 3.5014 1.4093 5.5000 5.5000 5.4314 0.5588 0.3031 0.0835 14.0362 0.1177 0.1039 0.3472 -0.0124 0.2228 3.7027 1.3840 5.5000 5.5000 5.4346 0.5494 0.2874 0.0825 13.3010 0.1141 0.0991 0.3328 -0.0131 0.2155 3.9040 1.3553 5.5000 5.5000 5.4374 0.5374 0.2713 0.0815 12.6377 0.1105 0.0941 0.3177 -0.0148 0.2071 4.1053 1.3232 5.5000 5.5000 5.4397 0.5232 0.2549 0.0807 12.0365 0.1068 0.0890 0.3021 -0.0172 0.1977 4.3067 1.2879 5.5000 5.5000 5.4416 0.5067 0.2383 0.0801 11.4892 0.1031 0.0838 0.2859 -0.0205 0.1875 4.5080 1.2495 5.5000 5.5000 5.4433 0.4880 0.2214 0.0796 10.9889 0.0994 0.0786 0.2692 -0.0245 0.1764 4.7093 1.2082 5.5000 5.5000 5.4431 0.4673 0.2044 0.0792 10.5299 0.0956 0.0734 0.2522 -0.0297 0.1646 4.9106 1.1641 5.5000 5.5000 5.4354 0.4446 0.1874 0.0789 10.1073 0.0918 0.0686 0.2348 -0.0371 0.1518 5.1119 1.1173 5.5000 5.5000 5.4193 0.4201 0.1703 0.0787 9.7170 0.0879 0.0642 0.2171 -0.0462 0.1381 5.3132 1.0680 5.5000 5.5000 5.3948 0.3939 0.1533 0.0786 9.3555 0.0839 0.0600 0.1993 -0.0567 0.1238 5.5145 1.0164 5.5000 5.5000 5.3624 0.3660 0.1364 0.0786 9.0196 0.0799 0.0558 0.1812 -0.0681 0.1092 5.7158 0.9625 5.5000 5.5000 5.3233 0.3365 0.1197 0.0786 8.7069 0.0757 0.0516 0.1632 -0.0797 0.0945 5.9171 0.9065 5.5000 5.5000 5.2792 0.3057 0.1033 0.0788 8.4150 0.0714 0.0473 0.1451 -0.0914 0.0798 6.1184 0.8485 5.5000 5.5000 5.2325 0.2735 0.0871 0.0790 8.1419 0.0670 0.0429 0.1270 -0.1027 0.0654 6.3198 0.7887 5.5000 5.5000 5.1863 0.2401 0.0713 0.0792 7.8859 0.0624 0.0383 0.1091 -0.1135 0.0512 6.5211 0.7272 5.5000 5.5000 5.1439 0.2055 0.0558 0.0794 7.6454 0.0578 0.0335 0.0914 -0.1238 0.0376 6.7224 0.6641 5.5000 5.5000 5.1093 0.1699 0.0409 0.0797 7.4190 0.0530 0.0287 0.0739 -0.1336 0.0244 6.9237 0.5997 5.5000 5.5000 5.0866 0.1334 0.0265 0.0800 7.2056 0.0480 0.0239 0.0568 -0.1428 0.0119 7.1165 0.5367 5.5000 5.5000 5.0489 0.0976 0.0132 0.0803 7.0124 0.0431 0.0195 0.0400 -0.1513 -0.0003 7.1629 0.5204 5.5000 5.5000 5.0178 0.0879 0.0100 0.0804 6.9674 0.0419 0.0184 0.0353 -0.1538 -0.0037 7.2008 0.5031 5.5000 5.5000 4.9848 0.0761 0.0069 0.0805 6.9311 0.0405 0.0173 0.0308 -0.1579 -0.0070 7.2386 0.4816 5.5000 5.5000 4.9471 0.0600 0.0033 0.0805 6.8952 0.0388 0.0159 0.0255 -0.1643 -0.0108 7.2765 0.4553 5.5000 5.5000 4.9091 0.0392 -0.0008 0.0806 6.8596 0.0367 0.0142 0.0194 -0.1732 -0.0150 7.3144 0.4232 5.5000 5.5000 4.8684 0.0127 -0.0055 0.0807 6.8244 0.0341 0.0123 0.0124 -0.1852 -0.0197 7.3523 0.3838 5.5000 5.5000 4.8294 -0.0210 -0.0111 0.0807 6.7896 0.0310 0.0102 0.0043 -0.2011 -0.0249 7.3902 0.3342 5.5000 5.5000 4.8047 -0.0649 -0.0177 0.0808 6.7551 0.0270 0.0078 -0.0051 -0.2224 -0.0308 7.4280 0.2672 5.5000 5.5000 4.8258 -0.1261 -0.0264 0.0808 6.7210 0.0216 0.0050 -0.0170 -0.2529 -0.0377 7.4659 0.1534 5.5000 5.5000 5.2721 -0.2336 -0.0404 0.0809 6.6872 0.0124 0.0017 -0.0354 -0.3083 -0.0477 7.5000 0.0204 5.5000 5.5028 5.5028 -0.3609 -0.0563 0.0809 6.6604 0.0017 0.0000 -0.0563 0.0000 0.0000 RADIUS: 7.50 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.17 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.083256 TOTAL WEIGHT (Kg) = 0.037758 TOTAL VOLUME (IN**3) = 1.356345 TOTAL PROJECTED AREA (IN**2) = 15.3837 MOMENT OF INERTIA (SNAIL-IN**2) = 0.002341 MOMENT OF INERTIA (Kg-M**2) = 0.000264 STATIC MOMENT, ONE SIDE (IN-LB) = 0.112381 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 = 87.535 INNER LIMIT (NORMALIZED BY RADIUS) = 0.053 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5932.82 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 4.57, E63 (Transition Start, Airfoil 1) AIRFOIL2: 7.43, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412