5x4E-3 (5x4E-3.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) 0.0004 0.4244 0.8698 0.0000 -0.0012 0.2122 0.0000 0.2112 0.0000 0.0896 0.0000 0.0900 0.0000 0.0000 0.0603 0.4150 1.0716 0.0093 -0.1916 0.2073 0.0059 0.2004 1.4103 0.0832 0.0712 0.0934 -0.0006 -0.0080 0.1200 0.4145 1.2664 0.0693 -0.3503 0.2056 0.0217 0.1901 5.2461 0.0788 0.0744 0.1026 -0.0011 -0.0051 0.1802 0.4242 1.4558 0.2136 -0.3884 0.2067 0.0449 0.1804 10.6821 0.0765 0.0749 0.1142 -0.0015 0.0008 0.2405 0.4449 1.6386 0.4541 -0.2403 0.2101 0.0728 0.1713 16.7245 0.0762 0.0720 0.1278 -0.0017 0.0095 0.3007 0.4753 1.8145 0.7816 0.1029 0.2153 0.1031 0.1628 22.4724 0.0774 0.0664 0.1433 -0.0015 0.0201 0.3609 0.5124 1.9835 1.1717 0.6079 0.2216 0.1332 0.1548 27.3268 0.0793 0.0590 0.1603 -0.0006 0.0321 0.4209 0.5518 2.1453 1.5896 1.2036 0.2287 0.1609 0.1474 31.0080 0.0814 0.0507 0.1776 0.0013 0.0448 0.4808 0.5887 2.3000 1.9948 1.7614 0.2360 0.1836 0.1406 33.4384 0.0828 0.0427 0.1935 0.0038 0.0568 0.5405 0.6186 2.4476 2.3432 2.2227 0.2430 0.1988 0.1344 34.6058 0.0831 0.0360 0.2052 0.0085 0.0684 0.6000 0.6372 2.5882 2.5872 2.5228 0.2492 0.2042 0.1287 34.4608 0.0820 0.0328 0.2096 0.0116 0.0750 0.6600 0.6507 2.7231 2.7231 2.6672 0.2561 0.2025 0.1235 33.2926 0.0804 0.0329 0.2083 0.0109 0.0756 0.7191 0.6619 2.8496 2.8496 2.8020 0.2619 0.2003 0.1189 32.2379 0.0787 0.0329 0.2065 0.0098 0.0755 0.7783 0.6710 2.9695 2.9695 2.9296 0.2667 0.1977 0.1148 31.2686 0.0770 0.0328 0.2043 0.0088 0.0753 0.8374 0.6782 3.0829 3.0829 3.0500 0.2706 0.1946 0.1112 30.3671 0.0754 0.0327 0.2018 0.0077 0.0747 0.8966 0.6836 3.1898 3.1898 3.1628 0.2736 0.1911 0.1081 29.5204 0.0739 0.0325 0.1988 0.0063 0.0737 0.9557 0.6871 3.2901 3.2901 3.2678 0.2757 0.1872 0.1054 28.7188 0.0724 0.0323 0.1954 0.0048 0.0724 1.0148 0.6889 3.3839 3.3839 3.3646 0.2769 0.1829 0.1033 27.9544 0.0711 0.0322 0.1917 0.0032 0.0709 1.0740 0.6891 3.4711 3.4711 3.4531 0.2774 0.1782 0.1016 27.2212 0.0700 0.0320 0.1877 0.0014 0.0691 1.1331 0.6876 3.5525 3.5525 3.5339 0.2770 0.1732 0.1003 26.5183 0.0690 0.0318 0.1834 -0.0005 0.0670 1.1922 0.6847 3.6303 3.6303 3.6093 0.2759 0.1679 0.0994 25.8558 0.0681 0.0316 0.1788 -0.0025 0.0647 1.2514 0.6803 3.7049 3.7049 3.6806 0.2741 0.1624 0.0986 25.2297 0.0671 0.0313 0.1739 -0.0046 0.0621 1.3105 0.6745 3.7760 3.7760 3.7479 0.2716 0.1567 0.0978 24.6352 0.0659 0.0309 0.1689 -0.0068 0.0593 1.3697 0.6674 3.8439 3.8439 3.8115 0.2685 0.1508 0.0969 24.0686 0.0647 0.0304 0.1636 -0.0091 0.0563 1.4288 0.6591 3.9084 3.9084 3.8713 0.2647 0.1447 0.0961 23.5267 0.0633 0.0298 0.1581 -0.0114 0.0531 1.4879 0.6497 3.9696 3.9696 3.9276 0.2603 0.1385 0.0953 23.0065 0.0619 0.0291 0.1524 -0.0138 0.0499 1.5471 0.6391 4.0275 4.0275 3.9802 0.2553 0.1322 0.0944 22.5058 0.0603 0.0283 0.1466 -0.0163 0.0466 1.6062 0.6275 4.0821 4.0821 4.0292 0.2498 0.1259 0.0936 22.0224 0.0587 0.0274 0.1407 -0.0187 0.0432 1.6653 0.6150 4.1333 4.1333 4.0749 0.2438 0.1195 0.0928 21.5546 0.0570 0.0265 0.1347 -0.0212 0.0399 1.7245 0.6016 4.1812 4.1812 4.1172 0.2373 0.1131 0.0919 21.1009 0.0553 0.0255 0.1286 -0.0236 0.0365 1.7836 0.5874 4.2257 4.2257 4.1565 0.2304 0.1067 0.0911 20.6598 0.0535 0.0244 0.1224 -0.0260 0.0332 1.8428 0.5724 4.2670 4.2670 4.1929 0.2231 0.1003 0.0902 20.2303 0.0517 0.0233 0.1162 -0.0284 0.0299 1.9019 0.5568 4.3049 4.3049 4.2263 0.2153 0.0940 0.0894 19.8111 0.0498 0.0221 0.1100 -0.0307 0.0267 1.9610 0.5406 4.3394 4.3394 4.2570 0.2072 0.0878 0.0886 19.4014 0.0479 0.0209 0.1037 -0.0330 0.0236 2.0202 0.5238 4.3707 4.3707 4.2852 0.1988 0.0817 0.0877 19.0004 0.0460 0.0197 0.0975 -0.0353 0.0206 2.0793 0.5066 4.3986 4.3986 4.3104 0.1901 0.0757 0.0869 18.6073 0.0440 0.0184 0.0914 -0.0375 0.0177 2.1384 0.4890 4.4232 4.4232 4.3332 0.1812 0.0698 0.0861 18.2214 0.0421 0.0172 0.0853 -0.0396 0.0149 2.1976 0.4711 4.4444 4.4444 4.3538 0.1720 0.0641 0.0852 17.8422 0.0402 0.0159 0.0793 -0.0417 0.0123 2.2567 0.4528 4.4624 4.4624 4.3722 0.1624 0.0585 0.0844 17.4692 0.0382 0.0147 0.0733 -0.0440 0.0097 2.3159 0.4243 4.4770 4.4770 4.3803 0.1431 0.0501 0.0836 17.1018 0.0355 0.0128 0.0639 -0.0511 0.0049 2.3726 0.3796 4.4879 4.4879 4.3801 0.1078 0.0374 0.0828 16.7544 0.0314 0.0102 0.0492 -0.0668 -0.0034 2.3876 0.3638 4.4902 4.4902 4.3813 0.0947 0.0330 0.0825 16.6630 0.0300 0.0094 0.0441 -0.0730 -0.0063 2.4003 0.3488 4.4921 4.4921 4.3827 0.0820 0.0289 0.0824 16.5865 0.0287 0.0086 0.0393 -0.0791 -0.0091 2.4129 0.3318 4.4937 4.4937 4.3850 0.0674 0.0242 0.0822 16.5103 0.0273 0.0078 0.0339 -0.0861 -0.0122 2.4255 0.3123 4.4952 4.4952 4.3893 0.0503 0.0188 0.0820 16.4342 0.0256 0.0069 0.0278 -0.0945 -0.0157 2.4381 0.2893 4.4966 4.4966 4.3972 0.0299 0.0125 0.0818 16.3584 0.0237 0.0060 0.0206 -0.1047 -0.0197 2.4508 0.2607 4.4978 4.4978 4.4133 0.0040 0.0047 0.0816 16.2828 0.0213 0.0049 0.0118 -0.1177 -0.0247 2.4634 0.2204 4.4989 4.4989 4.4525 -0.0331 -0.0063 0.0815 16.2073 0.0180 0.0035 -0.0004 -0.1367 -0.0316 2.4760 0.1582 4.4998 4.4998 4.5731 -0.0912 -0.0232 0.0813 16.1321 0.0129 0.0018 -0.0192 -0.1668 -0.0419 2.4886 0.0948 4.5006 4.5006 4.8798 -0.1506 -0.0404 0.0811 16.0571 0.0077 0.0007 -0.0380 -0.1974 -0.0522 2.5000 0.0377 4.5011 4.5033 4.5033 -0.2040 -0.0557 0.0809 15.9972 0.0031 0.0000 -0.0557 0.0000 0.0000 RADIUS: 2.50 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.60 HUB TRANSITION (IN) BLADES: 3 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.014014 TOTAL WEIGHT (Kg) = 0.006356 TOTAL VOLUME (IN**3) = 0.228310 TOTAL PROJECTED AREA (IN**2) = 3.6752 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000051 MOMENT OF INERTIA (Kg-M**2) = 0.000006 STATIC MOMENT, ONE SIDE (IN-LB) = 0.004627 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 = 160.646 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 28694.87 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.66, E63 (Transition Start, Airfoil 1) AIRFOIL2: 2.40, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412