13x4.5EP(F2B) (13x45EP(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 -1.8225 0.0000 0.0000 0.4000 0.0000 0.3562 0.0000 0.2850 0.0000 0.0350 0.0000 0.0000 0.0950 0.7690 -1.0470 0.0071 -0.3723 0.3953 0.0038 0.3548 0.6842 0.2729 0.1841 0.0384 0.0058 -0.0949 0.1900 0.7355 -0.3222 0.0559 -0.7213 0.3910 0.0141 0.3505 2.6798 0.2578 0.1792 0.0477 0.0189 -0.0895 0.2850 0.7035 0.3518 0.1852 -0.9754 0.3874 0.0297 0.3433 5.9042 0.2415 0.1717 0.0618 0.0339 -0.0808 0.3800 0.6775 0.9751 0.4292 -1.0229 0.3851 0.0491 0.3332 10.1914 0.2257 0.1578 0.0794 0.0504 -0.0687 0.4750 0.6616 1.5477 0.8100 -0.7869 0.3842 0.0709 0.3202 15.1835 0.2118 0.1408 0.0991 0.0673 -0.0538 0.5700 0.6584 2.0696 1.3280 -0.2332 0.3853 0.0939 0.3043 20.3455 0.2004 0.1232 0.1198 0.0834 -0.0368 0.6650 0.6687 2.5408 1.9526 0.6051 0.3885 0.1168 0.2856 25.0470 0.1910 0.1070 0.1402 0.0979 -0.0186 0.7600 0.6916 2.9612 2.6152 1.6016 0.3942 0.1381 0.2640 28.7080 0.1826 0.0934 0.1591 0.1099 -0.0002 0.8550 0.7252 3.3310 3.2168 2.4862 0.4027 0.1567 0.2395 30.9130 0.1737 0.0838 0.1752 0.1179 0.0163 0.9500 0.7679 3.6500 3.6489 3.0995 0.4144 0.1711 0.2121 31.4377 0.1628 0.0793 0.1875 0.1192 0.0276 1.0492 0.8162 3.9290 3.9290 3.5019 0.4282 0.1824 0.1804 30.7943 0.1472 0.0769 0.1967 0.1137 0.0342 1.2211 0.8908 4.2814 4.2814 4.0939 0.4491 0.1962 0.1309 29.1630 0.1166 0.0682 0.2082 0.1006 0.0442 1.3972 0.9556 4.4703 4.4703 4.4183 0.4668 0.2015 0.1042 26.9863 0.0996 0.0635 0.2139 0.0852 0.0522 1.5732 1.0090 4.5000 4.5000 4.4578 0.4808 0.1977 0.1000 24.4769 0.1009 0.0671 0.2135 0.0734 0.0591 1.7493 1.0520 4.5000 4.5000 4.4435 0.4912 0.1867 0.1000 22.2650 0.1052 0.0723 0.2070 0.0631 0.0595 1.9254 1.0857 4.5000 4.5000 4.4262 0.4983 0.1700 0.1000 20.4040 0.1086 0.0771 0.1949 0.0529 0.0530 2.1015 1.1106 4.5000 4.5000 4.4064 0.5022 0.1527 0.1000 18.8195 0.1111 0.0815 0.1821 0.0428 0.0450 2.2775 1.1273 4.5000 4.5000 4.3869 0.5031 0.1364 0.1000 17.4563 0.1127 0.0851 0.1698 0.0326 0.0370 2.4536 1.1361 4.5000 4.5000 4.3668 0.5011 0.1209 0.1000 16.2722 0.1136 0.0877 0.1581 0.0226 0.0292 2.6297 1.1378 4.5000 4.5000 4.3447 0.4964 0.1065 0.1000 15.2350 0.1138 0.0894 0.1468 0.0131 0.0219 2.8058 1.1326 4.5000 4.5000 4.3209 0.4891 0.0931 0.1000 14.3194 0.1133 0.0900 0.1360 0.0040 0.0151 2.9819 1.1213 4.5000 4.5000 4.2957 0.4794 0.0806 0.1000 13.5058 0.1121 0.0897 0.1257 -0.0046 0.0088 3.1579 1.1041 4.5000 4.5000 4.2697 0.4676 0.0691 0.1000 12.7781 0.1104 0.0884 0.1158 -0.0126 0.0030 3.3340 1.0818 4.5000 4.5000 4.2427 0.4537 0.0586 0.1000 12.1238 0.1082 0.0861 0.1062 -0.0201 -0.0021 3.5101 1.0547 4.5000 4.5000 4.2156 0.4378 0.0489 0.1000 11.5323 0.1055 0.0831 0.0971 -0.0270 -0.0067 3.6862 1.0234 4.5000 4.5000 4.1888 0.4203 0.0400 0.1000 10.9952 0.1023 0.0792 0.0884 -0.0334 -0.0108 3.8622 0.9884 4.5000 4.5000 4.1629 0.4012 0.0319 0.1000 10.5054 0.0988 0.0747 0.0800 -0.0392 -0.0143 4.0383 0.9501 4.5000 4.5000 4.1386 0.3807 0.0245 0.1000 10.0569 0.0950 0.0698 0.0719 -0.0446 -0.0174 4.2144 0.9092 4.5000 4.5000 4.1166 0.3589 0.0177 0.1000 9.6447 0.0909 0.0644 0.0641 -0.0497 -0.0200 4.3905 0.8661 4.5000 4.5000 4.0973 0.3360 0.0115 0.1000 9.2648 0.0866 0.0588 0.0566 -0.0544 -0.0223 4.5666 0.8212 4.5000 4.5000 4.0817 0.3123 0.0058 0.1000 8.9134 0.0821 0.0531 0.0494 -0.0590 -0.0243 4.7426 0.7752 4.5000 4.5000 4.0704 0.2878 0.0005 0.1000 8.5875 0.0775 0.0475 0.0424 -0.0635 -0.0261 4.9187 0.7285 4.5000 4.5000 4.0626 0.2626 -0.0044 0.1000 8.2844 0.0729 0.0420 0.0356 -0.0681 -0.0278 5.0948 0.6816 4.5000 4.5000 4.0569 0.2371 -0.0090 0.1000 8.0019 0.0682 0.0369 0.0290 -0.0730 -0.0295 5.2709 0.6351 4.5000 4.5000 4.0536 0.2113 -0.0134 0.1000 7.7379 0.0635 0.0321 0.0226 -0.0783 -0.0312 5.4469 0.5894 4.5000 4.5000 4.0525 0.1854 -0.0175 0.1000 7.4906 0.0589 0.0277 0.0163 -0.0840 -0.0330 5.6230 0.5450 4.5000 4.5000 4.0542 0.1596 -0.0215 0.1000 7.2586 0.0545 0.0238 0.0102 -0.0903 -0.0349 5.7991 0.5025 4.5000 4.5000 4.0548 0.1339 -0.0254 0.1000 7.0405 0.0503 0.0203 0.0041 -0.0971 -0.0371 5.9752 0.4623 4.5000 4.5000 4.0165 0.1087 -0.0293 0.1000 6.8350 0.0462 0.0172 -0.0028 -0.1045 -0.0404 6.1438 0.4266 4.5000 4.5000 3.9240 0.0850 -0.0330 0.1000 6.6491 0.0427 0.0147 -0.0102 -0.1123 -0.0444 6.1840 0.4185 4.5000 4.5000 3.8916 0.0795 -0.0339 0.1000 6.6063 0.0418 0.0142 -0.0120 -0.1142 -0.0455 6.2167 0.4101 4.5000 4.5000 3.8621 0.0731 -0.0349 0.1000 6.5719 0.0410 0.0136 -0.0138 -0.1168 -0.0466 6.2494 0.3979 4.5000 4.5000 3.8039 0.0628 -0.0363 0.1000 6.5378 0.0398 0.0129 -0.0163 -0.1216 -0.0480 6.2821 0.3813 4.5000 4.5000 3.7055 0.0480 -0.0382 0.1000 6.5040 0.0381 0.0118 -0.0195 -0.1289 -0.0499 6.3148 0.3595 4.5000 4.5000 3.6143 0.0280 -0.0407 0.1000 6.4706 0.0359 0.0105 -0.0235 -0.1391 -0.0522 6.3475 0.3310 4.5000 4.5000 3.5399 0.0012 -0.0440 0.1000 6.4376 0.0331 0.0089 -0.0285 -0.1530 -0.0549 6.3802 0.2929 4.5000 4.5000 3.5060 -0.0352 -0.0483 0.1000 6.4049 0.0293 0.0070 -0.0350 -0.1721 -0.0584 6.4129 0.2368 4.5000 4.5000 3.5965 -0.0897 -0.0547 0.1000 6.3725 0.0237 0.0046 -0.0442 -0.2011 -0.0632 6.4456 0.1298 4.5000 4.5000 4.4195 -0.1948 -0.0666 0.1000 6.3404 0.0130 0.0014 -0.0610 -0.2575 -0.0717 6.4750 0.0183 4.5000 4.5023 4.5023 -0.3047 -0.0789 0.1000 6.3150 0.0018 0.0000 -0.0789 0.0000 0.0000 RADIUS: 6.47 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) = 0.056601 TOTAL WEIGHT (Kg) = 0.025669 TOTAL VOLUME (IN**3) = 0.922099 TOTAL PROJECTED AREA (IN**2) = 10.4466 MOMENT OF INERTIA (SNAIL-IN**2) = 0.001229 MOMENT OF INERTIA (Kg-M**2) = 0.000139 STATIC MOMENT, ONE SIDE (IN-LB) = 0.067095 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 = 78.454 INNER LIMIT (NORMALIZED BY RADIUS) = 0.062 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 6183.08 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.95, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.76, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412