9x4.6SF (9x46SF.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 0.5000 0.2221 0.0000 0.0000 0.2500 0.0000 0.1170 0.0000 0.0585 0.0000 0.0500 0.0000 0.0000 0.0750 0.4928 0.5722 0.0086 -0.0814 0.2471 0.0048 0.1107 1.0406 0.0546 0.0421 0.0535 0.0010 0.0026 0.1500 0.4876 0.9045 0.0645 -0.1410 0.2460 0.0180 0.1048 3.9164 0.0511 0.0465 0.0624 0.0032 0.0038 0.2250 0.4866 1.2193 0.2034 -0.1052 0.2468 0.0373 0.0992 8.1891 0.0483 0.0475 0.0736 0.0070 0.0070 0.3000 0.4920 1.5172 0.4459 0.0795 0.2494 0.0608 0.0940 13.3082 0.0462 0.0458 0.0878 0.0122 0.0117 0.3750 0.5049 1.7985 0.7949 0.4357 0.2539 0.0865 0.0892 18.6430 0.0450 0.0421 0.1052 0.0185 0.0178 0.4500 0.5251 2.0636 1.2346 0.9467 0.2603 0.1125 0.0847 23.5882 0.0445 0.0373 0.1249 0.0259 0.0251 0.5250 0.5504 2.3131 1.7297 1.5343 0.2686 0.1369 0.0805 27.6703 0.0443 0.0321 0.1450 0.0341 0.0332 0.6000 0.5783 2.5472 2.2279 2.1297 0.2789 0.1575 0.0767 30.5819 0.0443 0.0272 0.1631 0.0432 0.0417 0.6750 0.6056 2.7665 2.6648 2.6435 0.2910 0.1726 0.0731 32.1424 0.0443 0.0232 0.1769 0.0523 0.0496 0.7500 0.6299 2.9714 2.9704 2.9869 0.3051 0.1801 0.0699 32.2249 0.0440 0.0211 0.1841 0.0594 0.0549 0.8273 0.6520 3.1678 3.1678 3.1991 0.3203 0.1821 0.0668 31.3595 0.0436 0.0207 0.1864 0.0636 0.0572 0.9440 0.6845 3.4373 3.4373 3.4806 0.3408 0.1840 0.0628 30.0940 0.0430 0.0206 0.1887 0.0679 0.0594 1.0629 0.7162 3.6800 3.6800 3.7246 0.3588 0.1846 0.0593 28.8552 0.0425 0.0213 0.1899 0.0703 0.0605 1.1819 0.7430 3.8919 3.8919 3.9370 0.3738 0.1842 0.0564 27.6584 0.0419 0.0220 0.1899 0.0718 0.0615 1.3009 0.7645 4.0748 4.0748 4.1202 0.3860 0.1826 0.0540 26.4980 0.0413 0.0224 0.1889 0.0726 0.0625 1.4198 0.7810 4.2304 4.2304 4.2763 0.3956 0.1799 0.0521 25.3708 0.0407 0.0227 0.1868 0.0728 0.0634 1.5388 0.7929 4.3605 4.3605 4.4069 0.4025 0.1763 0.0507 24.2752 0.0402 0.0229 0.1837 0.0725 0.0641 1.6578 0.8003 4.4666 4.4666 4.5138 0.4069 0.1717 0.0497 23.2107 0.0397 0.0229 0.1797 0.0716 0.0646 1.7767 0.8036 4.5506 4.5506 4.5985 0.4089 0.1663 0.0490 22.1773 0.0394 0.0228 0.1748 0.0703 0.0647 1.8957 0.8031 4.6141 4.6141 4.6630 0.4086 0.1600 0.0486 21.1754 0.0390 0.0226 0.1692 0.0684 0.0644 2.0147 0.7990 4.6588 4.6588 4.7089 0.4061 0.1530 0.0485 20.2058 0.0387 0.0224 0.1627 0.0661 0.0636 2.1336 0.7916 4.6866 4.6866 4.7380 0.4015 0.1453 0.0485 19.2691 0.0384 0.0220 0.1556 0.0631 0.0622 2.2526 0.7813 4.6990 4.6990 4.7521 0.3949 0.1370 0.0484 18.3662 0.0379 0.0214 0.1479 0.0595 0.0602 2.3716 0.7682 4.7000 4.7000 4.7552 0.3864 0.1282 0.0484 17.5062 0.0372 0.0207 0.1396 0.0552 0.0575 2.4905 0.7527 4.7000 4.7000 4.7578 0.3760 0.1189 0.0484 16.7177 0.0364 0.0199 0.1307 0.0502 0.0540 2.6095 0.7350 4.7000 4.7000 4.7609 0.3640 0.1092 0.0484 15.9954 0.0356 0.0190 0.1214 0.0445 0.0497 2.7284 0.7155 4.7000 4.7000 4.7646 0.3503 0.0992 0.0484 15.3314 0.0346 0.0181 0.1117 0.0380 0.0447 2.8474 0.6944 4.7000 4.7000 4.7689 0.3351 0.0889 0.0483 14.7193 0.0336 0.0170 0.1017 0.0308 0.0390 2.9664 0.6720 4.7000 4.7000 4.7740 0.3185 0.0784 0.0483 14.1531 0.0325 0.0160 0.0914 0.0228 0.0328 3.0853 0.6485 4.7000 4.7000 4.7798 0.3005 0.0677 0.0483 13.6281 0.0313 0.0150 0.0808 0.0139 0.0261 3.2043 0.6244 4.7000 4.7000 4.7864 0.2813 0.0569 0.0483 13.1401 0.0301 0.0139 0.0701 0.0043 0.0190 3.3233 0.5997 4.7000 4.7000 4.7937 0.2610 0.0461 0.0482 12.6852 0.0289 0.0129 0.0592 -0.0063 0.0116 3.4422 0.5749 4.7000 4.7000 4.8016 0.2397 0.0353 0.0482 12.2602 0.0277 0.0119 0.0483 -0.0178 0.0039 3.5612 0.5503 4.7000 4.7000 4.8105 0.2174 0.0245 0.0482 11.8625 0.0265 0.0110 0.0374 -0.0302 -0.0041 3.6802 0.5260 4.7000 4.7000 4.8204 0.1943 0.0138 0.0482 11.4894 0.0253 0.0101 0.0266 -0.0435 -0.0122 3.7991 0.5024 4.6983 4.6983 4.8296 0.1705 0.0033 0.0481 11.1348 0.0242 0.0092 0.0158 -0.0578 -0.0203 3.9181 0.4797 4.6799 4.6799 4.8225 0.1460 -0.0071 0.0481 10.7635 0.0231 0.0085 0.0053 -0.0731 -0.0285 4.0371 0.4583 4.6414 4.6414 4.7955 0.1210 -0.0173 0.0481 10.3692 0.0220 0.0078 -0.0051 -0.0894 -0.0365 4.1560 0.4384 4.5828 4.5828 4.7489 0.0956 -0.0273 0.0481 9.9538 0.0211 0.0072 -0.0151 -0.1067 -0.0443 4.2700 0.4017 4.5077 4.5077 4.6855 0.0517 -0.0398 0.0480 9.5376 0.0193 0.0061 -0.0282 -0.1344 -0.0541 4.2977 0.3867 4.4867 4.4867 4.6673 0.0348 -0.0437 0.0480 9.4336 0.0186 0.0056 -0.0325 -0.1446 -0.0573 4.3205 0.3722 4.4686 4.4686 4.6602 0.0186 -0.0473 0.0480 9.3477 0.0179 0.0052 -0.0364 -0.1545 -0.0602 4.3432 0.3553 4.4498 4.4498 4.6562 0.0000 -0.0513 0.0480 9.2612 0.0171 0.0048 -0.0408 -0.1657 -0.0634 4.3659 0.3356 4.4302 4.4302 4.6558 -0.0215 -0.0556 0.0480 9.1741 0.0161 0.0043 -0.0456 -0.1785 -0.0669 4.3886 0.3125 4.4100 4.4100 4.6611 -0.0465 -0.0605 0.0480 9.0863 0.0150 0.0037 -0.0511 -0.1933 -0.0709 4.4114 0.2848 4.3890 4.3890 4.6710 -0.0761 -0.0660 0.0480 8.9979 0.0137 0.0031 -0.0574 -0.2111 -0.0756 4.4341 0.2505 4.3672 4.3672 4.6690 -0.1122 -0.0727 0.0480 8.9089 0.0120 0.0026 -0.0648 -0.2345 -0.0821 4.4568 0.2054 4.3447 4.3447 4.6923 -0.1593 -0.0807 0.0480 8.8193 0.0099 0.0019 -0.0742 -0.2634 -0.0897 4.4795 0.1332 4.3215 4.3215 4.9317 -0.2332 -0.0925 0.0480 8.7291 0.0064 0.0008 -0.0883 -0.3044 -0.0994 4.5000 0.0196 4.3000 4.3046 4.3046 -0.3478 -0.1103 0.0480 8.6565 0.0009 0.0000 -0.1103 0.0000 0.0000 RADIUS: 4.51 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.75 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.010986 TOTAL WEIGHT (Kg) = 0.004983 TOTAL VOLUME (IN**3) = 0.178984 TOTAL PROJECTED AREA (IN**2) = 5.3200 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000117 MOMENT OF INERTIA (Kg-M**2) = 0.000013 STATIC MOMENT, ONE SIDE (IN-LB) = 0.009055 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 = 93.162 INNER LIMIT (NORMALIZED BY RADIUS) = 0.055 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 4413.17 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 4.40, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.50, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412