13x5.5MR (13x55MR.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 -10.5050 0.0000 0.0000 0.3250 0.0000 0.5190 0.0000 0.3373 0.0000 0.1350 0.0000 0.0000 0.1020 0.6408 -8.3832 0.0072 -0.2880 0.3216 0.0080 0.4664 0.6450 0.2989 0.1531 0.1399 0.0008 -0.0021 0.2040 0.6345 -6.4123 0.0558 -0.5424 0.3212 0.0300 0.4185 2.4945 0.2655 0.1521 0.1533 0.0039 0.0103 0.3060 0.6328 -4.5921 0.1830 -0.6866 0.3237 0.0626 0.3748 5.4383 0.2372 0.1481 0.1734 0.0091 0.0291 0.4080 0.6380 -2.9228 0.4178 -0.6291 0.3287 0.1028 0.3354 9.2557 0.2139 0.1395 0.1982 0.0161 0.0529 0.5100 0.6518 -1.4043 0.7755 -0.3239 0.3360 0.1476 0.2998 13.6052 0.1954 0.1281 0.2258 0.0244 0.0793 0.6120 0.6756 -0.0366 1.2570 0.2357 0.3452 0.1938 0.2680 18.1025 0.1810 0.1153 0.2545 0.0336 0.1062 0.7140 0.7096 1.1803 1.8473 1.0152 0.3560 0.2385 0.2396 22.3810 0.1700 0.1027 0.2826 0.0432 0.1318 0.8160 0.7532 2.2464 2.5172 1.8950 0.3681 0.2786 0.2146 26.1493 0.1616 0.0917 0.3085 0.0529 0.1538 0.9180 0.8051 3.1616 3.2261 2.7683 0.3812 0.3112 0.1926 29.2185 0.1551 0.0840 0.3305 0.0610 0.1692 1.0200 0.8635 3.9261 3.9265 3.5655 0.3950 0.3331 0.1735 31.4946 0.1498 0.0817 0.3465 0.0648 0.1737 1.1257 0.9252 4.5592 4.5592 4.2495 0.4092 0.3459 0.1565 32.8051 0.1448 0.0833 0.3573 0.0627 0.1700 1.2954 1.0135 5.2368 5.2368 5.0138 0.4294 0.3582 0.1346 32.7566 0.1364 0.0849 0.3689 0.0530 0.1688 1.4688 1.0899 5.4979 5.4979 5.3384 0.4470 0.3618 0.1182 30.7829 0.1288 0.0862 0.3737 0.0381 0.1736 1.6423 1.1525 5.5000 5.5000 5.3850 0.4617 0.3572 0.1067 28.0583 0.1230 0.0874 0.3714 0.0219 0.1796 1.8157 1.2014 5.5000 5.5000 5.4141 0.4735 0.3489 0.0991 25.7389 0.1191 0.0887 0.3655 0.0085 0.1827 1.9891 1.2368 5.5000 5.5000 5.4313 0.4824 0.3395 0.0945 23.7529 0.1169 0.0900 0.3587 -0.0020 0.1849 2.1625 1.2587 5.5000 5.5000 5.4389 0.4887 0.3290 0.0917 22.0372 0.1154 0.0907 0.3508 -0.0088 0.1863 2.3360 1.2673 5.5000 5.5000 5.4433 0.4923 0.3177 0.0897 20.5425 0.1136 0.0901 0.3421 -0.0123 0.1871 2.5094 1.2628 5.5000 5.5000 5.4481 0.4933 0.3058 0.0879 19.2304 0.1110 0.0878 0.3325 -0.0126 0.1871 2.6828 1.2506 5.5000 5.5000 5.4528 0.4920 0.2935 0.0863 18.0706 0.1079 0.0848 0.3221 -0.0119 0.1858 2.8562 1.2350 5.5000 5.5000 5.4570 0.4882 0.2807 0.0848 17.0388 0.1048 0.0815 0.3110 -0.0117 0.1831 3.0296 1.2162 5.5000 5.5000 5.4608 0.4822 0.2674 0.0836 16.1155 0.1016 0.0781 0.2992 -0.0121 0.1791 3.2031 1.1943 5.5000 5.5000 5.4642 0.4739 0.2537 0.0825 15.2849 0.0985 0.0745 0.2867 -0.0132 0.1738 3.3765 1.1694 5.5000 5.5000 5.4671 0.4636 0.2397 0.0816 14.5339 0.0954 0.0708 0.2737 -0.0150 0.1675 3.5499 1.1416 5.5000 5.5000 5.4696 0.4512 0.2254 0.0808 13.8519 0.0922 0.0670 0.2602 -0.0174 0.1603 3.7233 1.1111 5.5000 5.5000 5.4718 0.4369 0.2108 0.0801 13.2299 0.0890 0.0631 0.2463 -0.0204 0.1523 3.8968 1.0779 5.5000 5.5000 5.4695 0.4208 0.1960 0.0796 12.6605 0.0858 0.0594 0.2319 -0.0251 0.1431 4.0702 1.0422 5.5000 5.5000 5.4594 0.4029 0.1810 0.0792 12.1374 0.0826 0.0561 0.2172 -0.0317 0.1327 4.2436 1.0041 5.5000 5.5000 5.4415 0.3833 0.1659 0.0789 11.6553 0.0793 0.0531 0.2022 -0.0398 0.1214 4.4170 0.9638 5.5000 5.5000 5.4159 0.3622 0.1508 0.0788 11.2095 0.0759 0.0502 0.1869 -0.0489 0.1095 4.5904 0.9212 5.5000 5.5000 5.3837 0.3395 0.1357 0.0787 10.7961 0.0725 0.0473 0.1715 -0.0586 0.0972 4.7639 0.8766 5.5000 5.5000 5.3463 0.3155 0.1208 0.0787 10.4118 0.0690 0.0443 0.1560 -0.0684 0.0848 4.9373 0.8301 5.5000 5.5000 5.3057 0.2901 0.1059 0.0787 10.0537 0.0653 0.0410 0.1404 -0.0780 0.0724 5.1107 0.7818 5.5000 5.5000 5.2645 0.2635 0.0914 0.0789 9.7192 0.0616 0.0376 0.1248 -0.0871 0.0602 5.2841 0.7318 5.5000 5.5000 5.2258 0.2357 0.0771 0.0790 9.4060 0.0578 0.0339 0.1093 -0.0958 0.0484 5.4576 0.6802 5.5000 5.5000 5.1928 0.2069 0.0631 0.0793 9.1122 0.0539 0.0301 0.0938 -0.1039 0.0370 5.6310 0.6272 5.5000 5.5000 5.1689 0.1771 0.0496 0.0795 8.8361 0.0499 0.0261 0.0786 -0.1115 0.0261 5.8044 0.5728 5.5000 5.5000 5.1578 0.1465 0.0365 0.0798 8.5760 0.0457 0.0221 0.0635 -0.1187 0.0158 5.9778 0.5173 5.5000 5.5000 5.1635 0.1150 0.0240 0.0801 8.3308 0.0414 0.0182 0.0487 -0.1256 0.0059 6.1439 0.4630 5.5000 5.5000 5.1252 0.0842 0.0124 0.0804 8.1086 0.0372 0.0148 0.0336 -0.1322 -0.0045 6.1840 0.4490 5.5000 5.5000 5.0975 0.0759 0.0096 0.0805 8.0568 0.0361 0.0139 0.0296 -0.1342 -0.0074 6.2167 0.4342 5.5000 5.5000 5.0694 0.0657 0.0068 0.0806 8.0150 0.0350 0.0130 0.0256 -0.1377 -0.0101 6.2494 0.4157 5.5000 5.5000 5.0373 0.0520 0.0036 0.0806 7.9736 0.0335 0.0120 0.0210 -0.1430 -0.0133 6.2821 0.3930 5.5000 5.5000 5.0083 0.0341 -0.0002 0.0807 7.9326 0.0317 0.0107 0.0156 -0.1506 -0.0169 6.3148 0.3654 5.5000 5.5000 4.9799 0.0113 -0.0046 0.0807 7.8920 0.0295 0.0093 0.0095 -0.1608 -0.0209 6.3475 0.3314 5.5000 5.5000 4.9571 -0.0177 -0.0098 0.0808 7.8519 0.0268 0.0077 0.0023 -0.1744 -0.0254 6.3802 0.2886 5.5000 5.5000 4.9532 -0.0555 -0.0162 0.0809 7.8122 0.0233 0.0059 -0.0062 -0.1926 -0.0305 6.4129 0.2308 5.5000 5.5000 5.0108 -0.1081 -0.0246 0.0809 7.7728 0.0187 0.0038 -0.0170 -0.2187 -0.0367 6.4456 0.1327 5.5000 5.5000 5.4844 -0.2007 -0.0382 0.0810 7.7338 0.0107 0.0013 -0.0342 -0.2660 -0.0459 6.4750 0.0176 5.5000 5.5028 5.5028 -0.3106 -0.0539 0.0810 7.7030 0.0014 0.0000 -0.0539 0.0000 0.0000 RADIUS: 6.47 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 1.02 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.054915 TOTAL WEIGHT (Kg) = 0.024905 TOTAL VOLUME (IN**3) = 0.894638 TOTAL PROJECTED AREA (IN**2) = 11.2837 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001159 MOMENT OF INERTIA (Kg-M**2) = 0.000131 STATIC MOMENT, ONE SIDE (IN-LB) = 0.064126 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 = 87.518 INNER LIMIT (NORMALIZED BY RADIUS) = 0.050 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 6895.00 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 3.70, E63 (Transition Start, Airfoil 1) AIRFOIL2: 6.00, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412