14x5.5MR (14x55MR.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 -10.5000 0.0000 0.0000 0.3250 0.0000 0.5192 0.0000 0.3375 0.0000 0.1400 0.0000 0.0000 0.1100 0.6417 -8.3756 0.0079 -0.3103 0.3220 0.0085 0.4668 0.6544 0.2996 0.1561 0.1454 0.0009 0.0006 0.2200 0.6393 -6.4025 0.0608 -0.5802 0.3236 0.0317 0.4189 2.5184 0.2678 0.1562 0.1603 0.0041 0.0142 0.3300 0.6441 -4.5806 0.1976 -0.7211 0.3292 0.0663 0.3753 5.4446 0.2417 0.1534 0.1827 0.0094 0.0350 0.4400 0.6573 -2.9100 0.4455 -0.6454 0.3382 0.1090 0.3359 9.1545 0.2208 0.1465 0.2105 0.0167 0.0609 0.5500 0.6804 -1.3906 0.8157 -0.3156 0.3498 0.1566 0.3004 13.2807 0.2044 0.1369 0.2413 0.0253 0.0899 0.6600 0.7137 -0.0225 1.3038 0.2630 0.3635 0.2059 0.2685 17.4537 0.1917 0.1256 0.2734 0.0350 0.1196 0.7700 0.7569 1.1944 1.8920 1.0473 0.3787 0.2538 0.2402 21.3585 0.1818 0.1142 0.3046 0.0453 0.1481 0.8800 0.8089 2.2600 2.5514 1.9066 0.3947 0.2969 0.2151 24.7705 0.1740 0.1039 0.3331 0.0556 0.1728 0.9900 0.8679 3.1744 3.2464 2.7576 0.4109 0.3322 0.1932 27.5602 0.1676 0.0966 0.3570 0.0642 0.1909 1.1000 0.9321 3.9375 3.9380 3.5418 0.4267 0.3564 0.1740 29.6736 0.1622 0.0946 0.3743 0.0677 0.1974 1.2140 0.9987 4.5690 4.5690 4.2271 0.4420 0.3711 0.1570 30.9204 0.1568 0.0969 0.3860 0.0639 0.1949 1.3976 1.0942 5.2439 5.2439 4.9925 0.4639 0.3850 0.1349 30.8444 0.1477 0.0986 0.3987 0.0533 0.1955 1.5852 1.1769 5.4986 5.4986 5.3151 0.4830 0.3889 0.1184 28.9020 0.1393 0.1002 0.4040 0.0374 0.2015 1.7728 1.2447 5.5000 5.5000 5.3647 0.4990 0.3838 0.1068 26.2792 0.1330 0.1016 0.4016 0.0206 0.2080 1.9603 1.2978 5.5000 5.5000 5.3965 0.5117 0.3746 0.0992 24.0622 0.1288 0.1031 0.3953 0.0068 0.2108 2.1479 1.3362 5.5000 5.5000 5.4151 0.5215 0.3641 0.0945 22.1725 0.1263 0.1046 0.3879 -0.0039 0.2125 2.3355 1.3601 5.5000 5.5000 5.4232 0.5282 0.3525 0.0917 20.5460 0.1247 0.1054 0.3794 -0.0107 0.2132 2.5231 1.3697 5.5000 5.5000 5.4278 0.5322 0.3400 0.0897 19.1334 0.1228 0.1047 0.3700 -0.0140 0.2131 2.7107 1.3650 5.5000 5.5000 5.4327 0.5334 0.3272 0.0879 17.8966 0.1199 0.1022 0.3596 -0.0139 0.2123 2.8983 1.3520 5.5000 5.5000 5.4375 0.5319 0.3138 0.0863 16.8056 0.1166 0.0986 0.3484 -0.0127 0.2102 3.0859 1.3353 5.5000 5.5000 5.4417 0.5279 0.2999 0.0848 15.8368 0.1133 0.0948 0.3363 -0.0122 0.2065 3.2734 1.3152 5.5000 5.5000 5.4455 0.5214 0.2856 0.0836 14.9712 0.1099 0.0908 0.3236 -0.0124 0.2014 3.4610 1.2916 5.5000 5.5000 5.4488 0.5125 0.2709 0.0825 14.1934 0.1065 0.0867 0.3101 -0.0134 0.1951 3.6486 1.2647 5.5000 5.5000 5.4516 0.5013 0.2558 0.0815 13.4910 0.1031 0.0823 0.2961 -0.0151 0.1877 3.8362 1.2348 5.5000 5.5000 5.4540 0.4879 0.2404 0.0808 12.8538 0.0997 0.0779 0.2814 -0.0175 0.1794 4.0238 1.2018 5.5000 5.5000 5.4560 0.4725 0.2247 0.0801 12.2731 0.0963 0.0734 0.2663 -0.0207 0.1702 4.2114 1.1659 5.5000 5.5000 5.4530 0.4551 0.2089 0.0796 11.7420 0.0928 0.0691 0.2508 -0.0256 0.1598 4.3990 1.1273 5.5000 5.5000 5.4416 0.4357 0.1928 0.0792 11.2543 0.0893 0.0653 0.2349 -0.0327 0.1482 4.5866 1.0861 5.5000 5.5000 5.4217 0.4146 0.1767 0.0789 10.8051 0.0857 0.0618 0.2187 -0.0415 0.1358 4.7741 1.0424 5.5000 5.5000 5.3937 0.3917 0.1606 0.0787 10.3899 0.0821 0.0584 0.2022 -0.0514 0.1227 4.9617 0.9964 5.5000 5.5000 5.3583 0.3672 0.1445 0.0786 10.0052 0.0784 0.0550 0.1855 -0.0619 0.1092 5.1493 0.9482 5.5000 5.5000 5.3170 0.3412 0.1286 0.0786 9.6477 0.0745 0.0514 0.1687 -0.0726 0.0955 5.3369 0.8978 5.5000 5.5000 5.2721 0.3138 0.1128 0.0787 9.3147 0.0706 0.0477 0.1519 -0.0831 0.0819 5.5245 0.8456 5.5000 5.5000 5.2264 0.2850 0.0972 0.0788 9.0036 0.0666 0.0437 0.1350 -0.0931 0.0685 5.7121 0.7914 5.5000 5.5000 5.1830 0.2550 0.0820 0.0790 8.7126 0.0625 0.0394 0.1182 -0.1025 0.0555 5.8997 0.7356 5.5000 5.5000 5.1455 0.2238 0.0671 0.0792 8.4396 0.0583 0.0350 0.1015 -0.1113 0.0430 6.0872 0.6783 5.5000 5.5000 5.1176 0.1916 0.0526 0.0795 8.1831 0.0539 0.0304 0.0850 -0.1196 0.0309 6.2748 0.6195 5.5000 5.5000 5.1028 0.1584 0.0386 0.0798 7.9416 0.0494 0.0257 0.0687 -0.1275 0.0194 6.4624 0.5594 5.5000 5.5000 5.1047 0.1244 0.0251 0.0801 7.7139 0.0448 0.0212 0.0527 -0.1350 0.0085 6.6421 0.5008 5.5000 5.5000 5.0784 0.0911 0.0127 0.0804 7.5077 0.0403 0.0172 0.0367 -0.1422 -0.0026 6.6854 0.4856 5.5000 5.5000 5.0505 0.0820 0.0096 0.0805 7.4596 0.0391 0.0162 0.0323 -0.1444 -0.0057 6.7207 0.4695 5.5000 5.5000 5.0210 0.0710 0.0067 0.0805 7.4208 0.0378 0.0151 0.0281 -0.1481 -0.0087 6.7561 0.4494 5.5000 5.5000 4.9872 0.0561 0.0033 0.0806 7.3824 0.0362 0.0139 0.0231 -0.1540 -0.0122 6.7914 0.4249 5.5000 5.5000 4.9543 0.0367 -0.0006 0.0806 7.3444 0.0343 0.0125 0.0173 -0.1622 -0.0161 6.8268 0.3950 5.5000 5.5000 4.9201 0.0120 -0.0052 0.0807 7.3068 0.0319 0.0108 0.0107 -0.1733 -0.0204 6.8621 0.3582 5.5000 5.5000 4.8895 -0.0194 -0.0106 0.0807 7.2696 0.0289 0.0089 0.0031 -0.1881 -0.0253 6.8975 0.3119 5.5000 5.5000 4.8752 -0.0604 -0.0172 0.0808 7.2327 0.0252 0.0068 -0.0058 -0.2079 -0.0308 6.9328 0.2494 5.5000 5.5000 4.9124 -0.1174 -0.0257 0.0809 7.1962 0.0202 0.0044 -0.0172 -0.2363 -0.0374 6.9682 0.1433 5.5000 5.5000 5.3733 -0.2177 -0.0395 0.0809 7.1601 0.0116 0.0015 -0.0350 -0.2877 -0.0470 7.0000 0.0191 5.5000 5.5028 5.5028 -0.3364 -0.0553 0.0810 7.1314 0.0015 0.0000 -0.0553 0.0000 0.0000 RADIUS: 7.00 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 1.10 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.067422 TOTAL WEIGHT (Kg) = 0.030577 TOTAL VOLUME (IN**3) = 1.098399 TOTAL PROJECTED AREA (IN**2) = 13.2226 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001701 MOMENT OF INERTIA (Kg-M**2) = 0.000192 STATIC MOMENT, ONE SIDE (IN-LB) = 0.086848 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 = 87.540 INNER LIMIT (NORMALIZED BY RADIUS) = 0.046 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 6273.47 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 4.00, E63 (Transition Start, Airfoil 1) AIRFOIL2: 6.50, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412