10x4.6SF (10x46SF.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 0.2218 0.0000 0.0000 0.2500 0.0000 0.1794 0.0000 0.0897 0.0000 0.0800 0.0000 0.0000 0.0800 0.4933 0.5616 0.0089 -0.1551 0.2471 0.0050 0.1680 1.0182 0.0829 0.0681 0.0829 0.0005 0.0006 0.1600 0.4902 0.8846 0.0670 -0.2746 0.2466 0.0186 0.1573 3.8147 0.0771 0.0700 0.0901 0.0022 0.0029 0.2400 0.4924 1.1912 0.2098 -0.2777 0.2482 0.0386 0.1473 7.9210 0.0725 0.0684 0.0995 0.0055 0.0075 0.3200 0.5017 1.4818 0.4556 -0.1122 0.2520 0.0629 0.1381 12.7674 0.0693 0.0642 0.1111 0.0100 0.0140 0.4000 0.5185 1.7567 0.8040 0.2394 0.2579 0.0895 0.1295 17.7406 0.0672 0.0582 0.1250 0.0158 0.0220 0.4800 0.5421 2.0165 1.2362 0.7589 0.2657 0.1164 0.1216 22.2884 0.0659 0.0512 0.1408 0.0230 0.0314 0.5600 0.5703 2.2613 1.7163 1.3777 0.2755 0.1416 0.1143 26.0023 0.0652 0.0438 0.1573 0.0317 0.0419 0.6400 0.6004 2.4917 2.1950 1.9798 0.2871 0.1630 0.1076 28.6280 0.0646 0.0370 0.1730 0.0419 0.0528 0.7200 0.6294 2.7080 2.6138 2.5007 0.3004 0.1786 0.1015 30.0183 0.0639 0.0317 0.1856 0.0527 0.0630 0.8000 0.6546 2.9107 2.9098 2.8627 0.3154 0.1864 0.0960 30.0659 0.0628 0.0289 0.1925 0.0615 0.0698 0.8828 0.6774 3.1064 3.1064 3.0936 0.3313 0.1886 0.0908 29.2507 0.0615 0.0283 0.1950 0.0668 0.0727 1.0134 0.7124 3.3874 3.3874 3.4059 0.3539 0.1908 0.0837 28.0116 0.0596 0.0280 0.1977 0.0728 0.0759 1.1469 0.7469 3.6407 3.6407 3.6668 0.3736 0.1917 0.0776 26.8040 0.0580 0.0285 0.1992 0.0761 0.0774 1.2803 0.7765 3.8618 3.8618 3.8911 0.3902 0.1913 0.0727 25.6430 0.0565 0.0291 0.1995 0.0781 0.0784 1.4138 0.8004 4.0524 4.0524 4.0847 0.4037 0.1897 0.0689 24.5220 0.0551 0.0295 0.1985 0.0794 0.0794 1.5472 0.8187 4.2144 4.2144 4.2488 0.4142 0.1869 0.0659 23.4371 0.0540 0.0298 0.1964 0.0801 0.0802 1.6807 0.8319 4.3496 4.3496 4.3857 0.4219 0.1830 0.0638 22.3861 0.0530 0.0299 0.1932 0.0802 0.0806 1.8141 0.8403 4.4597 4.4597 4.4965 0.4268 0.1781 0.0623 21.3681 0.0523 0.0298 0.1890 0.0797 0.0807 1.9476 0.8441 4.5467 4.5467 4.5841 0.4291 0.1722 0.0613 20.3827 0.0517 0.0297 0.1839 0.0786 0.0803 2.0810 0.8438 4.6123 4.6123 4.6504 0.4289 0.1654 0.0608 19.4301 0.0513 0.0295 0.1778 0.0770 0.0793 2.2145 0.8395 4.6584 4.6584 4.6972 0.4263 0.1577 0.0605 18.5105 0.0508 0.0291 0.1710 0.0748 0.0777 2.3479 0.8317 4.6867 4.6867 4.7265 0.4213 0.1493 0.0605 17.6245 0.0503 0.0285 0.1634 0.0718 0.0753 2.4814 0.8206 4.6991 4.6991 4.7403 0.4142 0.1402 0.0605 16.7727 0.0496 0.0278 0.1551 0.0681 0.0722 2.6148 0.8065 4.7000 4.7000 4.7430 0.4049 0.1305 0.0604 15.9643 0.0487 0.0269 0.1462 0.0636 0.0684 2.7483 0.7898 4.7000 4.7000 4.7453 0.3937 0.1203 0.0604 15.2260 0.0477 0.0258 0.1367 0.0583 0.0637 2.8817 0.7708 4.7000 4.7000 4.7482 0.3806 0.1098 0.0604 14.5515 0.0465 0.0246 0.1267 0.0522 0.0583 3.0152 0.7497 4.7000 4.7000 4.7517 0.3658 0.0990 0.0604 13.9331 0.0453 0.0233 0.1163 0.0452 0.0522 3.1486 0.7270 4.7000 4.7000 4.7560 0.3493 0.0879 0.0603 13.3642 0.0439 0.0220 0.1055 0.0373 0.0454 3.2821 0.7029 4.7000 4.7000 4.7610 0.3312 0.0766 0.0603 12.8392 0.0424 0.0206 0.0944 0.0286 0.0381 3.4155 0.6777 4.7000 4.7000 4.7668 0.3118 0.0652 0.0603 12.3532 0.0409 0.0192 0.0831 0.0188 0.0304 3.5490 0.6518 4.7000 4.7000 4.7735 0.2910 0.0537 0.0603 11.9022 0.0393 0.0178 0.0716 0.0082 0.0222 3.6824 0.6255 4.7000 4.7000 4.7806 0.2690 0.0421 0.0602 11.4826 0.0377 0.0165 0.0600 -0.0035 0.0138 3.8159 0.5990 4.7000 4.7000 4.7888 0.2459 0.0306 0.0602 11.0911 0.0361 0.0152 0.0483 -0.0161 0.0051 3.9493 0.5727 4.7000 4.7000 4.7980 0.2218 0.0192 0.0602 10.7252 0.0345 0.0139 0.0366 -0.0298 -0.0038 4.0828 0.5469 4.7000 4.7000 4.8084 0.1968 0.0079 0.0602 10.3824 0.0329 0.0128 0.0250 -0.0445 -0.0128 4.2162 0.5220 4.6951 4.6951 4.8148 0.1710 -0.0032 0.0601 10.0503 0.0314 0.0117 0.0136 -0.0603 -0.0219 4.3497 0.4982 4.6703 4.6703 4.8013 0.1446 -0.0142 0.0601 9.6975 0.0299 0.0107 0.0024 -0.0772 -0.0308 4.4831 0.4758 4.6246 4.6246 4.7676 0.1176 -0.0249 0.0601 9.3236 0.0286 0.0098 -0.0086 -0.0952 -0.0395 4.6166 0.4552 4.5580 4.5580 4.7135 0.0902 -0.0354 0.0601 8.9302 0.0273 0.0090 -0.0192 -0.1144 -0.0481 4.7444 0.4220 4.4746 4.4746 4.6421 0.0484 -0.0474 0.0600 8.5366 0.0253 0.0078 -0.0319 -0.1420 -0.0580 4.7753 0.4073 4.4515 4.4515 4.6219 0.0313 -0.0512 0.0600 8.4391 0.0244 0.0073 -0.0361 -0.1527 -0.0612 4.8005 0.3928 4.4318 4.4318 4.6115 0.0148 -0.0547 0.0600 8.3588 0.0236 0.0068 -0.0400 -0.1629 -0.0641 4.8258 0.3757 4.4114 4.4114 4.5969 -0.0044 -0.0585 0.0600 8.2778 0.0226 0.0063 -0.0444 -0.1755 -0.0676 4.8510 0.3556 4.3902 4.3902 4.5695 -0.0267 -0.0628 0.0600 8.1964 0.0213 0.0059 -0.0493 -0.1908 -0.0719 4.8763 0.3317 4.3683 4.3683 4.5273 -0.0528 -0.0675 0.0600 8.1143 0.0199 0.0054 -0.0548 -0.2086 -0.0768 4.9015 0.3029 4.3456 4.3456 4.4861 -0.0839 -0.0730 0.0600 8.0317 0.0182 0.0047 -0.0612 -0.2288 -0.0822 4.9268 0.2671 4.3222 4.3222 4.4651 -0.1220 -0.0793 0.0600 7.9485 0.0160 0.0038 -0.0687 -0.2520 -0.0881 4.9520 0.2198 4.2980 4.2980 4.5042 -0.1717 -0.0869 0.0600 7.8649 0.0132 0.0026 -0.0782 -0.2805 -0.0947 4.9773 0.1447 4.2731 4.2731 4.7599 -0.2490 -0.0981 0.0600 7.7806 0.0087 0.0012 -0.0923 -0.3228 -0.1037 5.0000 0.0204 4.2500 4.2548 4.2548 -0.3749 -0.1156 0.0600 7.7129 0.0012 0.0000 -0.1156 0.0000 0.0000 RADIUS: 5.01 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.80 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.016306 TOTAL WEIGHT (Kg) = 0.007395 TOTAL VOLUME (IN**3) = 0.265645 TOTAL PROJECTED AREA (IN**2) = 6.2359 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000207 MOMENT OF INERTIA (Kg-M**2) = 0.000023 STATIC MOMENT, ONE SIDE (IN-LB) = 0.014459 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 = 87.306 INNER LIMIT (NORMALIZED BY RADIUS) = 0.050 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 4456.81 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 4.80, E63 (Transition Start, Airfoil 1) AIRFOIL2: 5.00, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412