9x4.7SF (9x47SF.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 -1.7200 0.0000 0.0000 0.2500 0.0000 0.0937 0.0000 0.0468 0.0000 0.0400 0.0000 0.0000 0.0750 0.4799 -1.2475 0.0045 -0.3765 0.2498 0.0060 0.0899 0.5473 0.0432 0.0950 0.0451 0.0070 -0.0663 0.1500 0.4649 -0.7931 0.0352 -0.7208 0.2558 0.0224 0.0863 2.1404 0.0401 0.0903 0.0588 0.0208 -0.0512 0.2250 0.4556 -0.3568 0.1149 -0.9719 0.2672 0.0464 0.0828 4.6483 0.0377 0.0857 0.0788 0.0375 -0.0292 0.3000 0.4530 0.0615 0.2613 -1.0343 0.2829 0.0751 0.0795 7.8931 0.0360 0.0783 0.1015 0.0564 -0.0028 0.3750 0.4576 0.4618 0.4819 -0.8528 0.3018 0.1061 0.0763 11.5592 0.0349 0.0686 0.1257 0.0765 0.0255 0.4500 0.4699 0.8440 0.7722 -0.4301 0.3230 0.1368 0.0733 15.2752 0.0344 0.0578 0.1507 0.0970 0.0531 0.5250 0.4894 1.2081 1.1161 0.1795 0.3454 0.1647 0.0703 18.6933 0.0344 0.0471 0.1746 0.1173 0.0777 0.6000 0.5154 1.5542 1.4883 0.8785 0.3681 0.1873 0.0676 21.5438 0.0348 0.0377 0.1949 0.1368 0.0966 0.6750 0.5467 1.8822 1.8578 1.5316 0.3901 0.2022 0.0650 23.6557 0.0355 0.0312 0.2084 0.1543 0.1074 0.7500 0.5823 2.1922 2.1919 1.9726 0.4104 0.2067 0.0625 24.9452 0.0364 0.0295 0.2124 0.1658 0.1059 0.8273 0.6204 2.4927 2.4927 2.2827 0.4295 0.2039 0.0601 25.6202 0.0373 0.0317 0.2096 0.1708 0.0948 0.9440 0.6751 2.9101 2.9101 2.7264 0.4563 0.1996 0.0568 26.1348 0.0383 0.0343 0.2054 0.1765 0.0806 1.0629 0.7272 3.2907 3.2907 3.1428 0.4813 0.1952 0.0537 26.2302 0.0391 0.0361 0.2012 0.1805 0.0688 1.1819 0.7754 3.6258 3.6258 3.5157 0.5041 0.1908 0.0511 26.0240 0.0396 0.0372 0.1972 0.1828 0.0593 1.3009 0.8199 3.9155 3.9155 3.8410 0.5245 0.1865 0.0488 25.5964 0.0400 0.0376 0.1933 0.1836 0.0520 1.4198 0.8604 4.1598 4.1598 4.1162 0.5425 0.1821 0.0468 24.9990 0.0403 0.0376 0.1895 0.1830 0.0465 1.5388 0.8969 4.3586 4.3586 4.3401 0.5583 0.1776 0.0452 24.2660 0.0406 0.0372 0.1856 0.1813 0.0426 1.6578 0.9295 4.5120 4.5120 4.5148 0.5717 0.1730 0.0440 23.4213 0.0409 0.0365 0.1817 0.1786 0.0404 1.7767 0.9580 4.6200 4.6200 4.6403 0.5828 0.1683 0.0431 22.4821 0.0413 0.0359 0.1777 0.1753 0.0395 1.8957 0.9823 4.6825 4.6825 4.7144 0.5916 0.1633 0.0426 21.4612 0.0419 0.0352 0.1737 0.1714 0.0398 2.0147 1.0025 4.7000 4.7000 4.7392 0.5980 0.1581 0.0425 20.3696 0.0426 0.0348 0.1694 0.1673 0.0413 2.1336 1.0184 4.7000 4.7000 4.7445 0.6021 0.1526 0.0425 19.3202 0.0433 0.0345 0.1651 0.1631 0.0429 2.2526 1.0299 4.7000 4.7000 4.7480 0.6039 0.1470 0.0425 18.3701 0.0438 0.0342 0.1605 0.1588 0.0441 2.3716 1.0371 4.7000 4.7000 4.7501 0.6033 0.1412 0.0425 17.5062 0.0441 0.0341 0.1556 0.1542 0.0448 2.4905 1.0399 4.7000 4.7000 4.7507 0.6005 0.1352 0.0425 16.7177 0.0442 0.0340 0.1505 0.1494 0.0450 2.6095 1.0382 4.7000 4.7000 4.7508 0.5953 0.1289 0.0425 15.9954 0.0441 0.0339 0.1450 0.1442 0.0446 2.7284 1.0320 4.7000 4.7000 4.7512 0.5877 0.1223 0.0425 15.3314 0.0439 0.0335 0.1392 0.1387 0.0438 2.8474 1.0211 4.7000 4.7000 4.7521 0.5779 0.1154 0.0425 14.7193 0.0434 0.0328 0.1329 0.1328 0.0425 2.9664 1.0056 4.7000 4.7000 4.7534 0.5657 0.1082 0.0425 14.1531 0.0427 0.0318 0.1263 0.1266 0.0407 3.0853 0.9854 4.7000 4.7000 4.7553 0.5512 0.1006 0.0425 13.6281 0.0419 0.0305 0.1191 0.1200 0.0383 3.2043 0.9604 4.7000 4.7000 4.7579 0.5343 0.0927 0.0425 13.1401 0.0408 0.0291 0.1115 0.1131 0.0354 3.3233 0.9305 4.7000 4.7000 4.7614 0.5152 0.0844 0.0425 12.6852 0.0395 0.0274 0.1033 0.1059 0.0320 3.4422 0.8957 4.7000 4.7000 4.7659 0.4937 0.0757 0.0425 12.2602 0.0381 0.0254 0.0946 0.0984 0.0279 3.5612 0.8560 4.7000 4.7000 4.7717 0.4699 0.0665 0.0425 11.8625 0.0364 0.0233 0.0852 0.0906 0.0232 3.6802 0.8113 4.7000 4.7000 4.7794 0.4437 0.0568 0.0425 11.4894 0.0345 0.0211 0.0751 0.0826 0.0178 3.7991 0.7615 4.6970 4.6970 4.7861 0.4152 0.0467 0.0425 11.1318 0.0324 0.0187 0.0644 0.0744 0.0118 3.9181 0.7066 4.6648 4.6648 4.7659 0.3844 0.0359 0.0425 10.7296 0.0300 0.0162 0.0529 0.0660 0.0054 4.0371 0.6464 4.5975 4.5975 4.7147 0.3513 0.0245 0.0425 10.2732 0.0275 0.0138 0.0407 0.0574 -0.0016 4.1560 0.5811 4.4949 4.4949 4.6333 0.3159 0.0124 0.0425 9.7667 0.0247 0.0113 0.0277 0.0487 -0.0092 4.2700 0.5081 4.3636 4.3636 4.5305 0.2744 -0.0006 0.0425 9.2380 0.0216 0.0088 0.0134 0.0376 -0.0179 4.2977 0.4838 4.3268 4.3268 4.5021 0.2583 -0.0048 0.0425 9.1032 0.0206 0.0080 0.0087 0.0319 -0.0209 4.3205 0.4611 4.2952 4.2952 4.4777 0.2424 -0.0086 0.0425 8.9910 0.0196 0.0073 0.0044 0.0259 -0.0236 4.3432 0.4353 4.2623 4.2623 4.4528 0.2236 -0.0128 0.0425 8.8773 0.0185 0.0066 -0.0004 0.0185 -0.0267 4.3659 0.4058 4.2281 4.2281 4.4389 0.2012 -0.0176 0.0425 8.7621 0.0172 0.0057 -0.0059 0.0089 -0.0304 4.3886 0.3715 4.1926 4.1926 4.4322 0.1742 -0.0230 0.0425 8.6454 0.0158 0.0049 -0.0122 -0.0031 -0.0346 4.4114 0.3301 4.1559 4.1559 4.4338 0.1403 -0.0294 0.0425 8.5272 0.0140 0.0039 -0.0196 -0.0192 -0.0398 4.4341 0.2767 4.1178 4.1178 4.4384 0.0946 -0.0376 0.0425 8.4076 0.0118 0.0030 -0.0292 -0.0437 -0.0474 4.4568 0.1950 4.0785 4.0785 4.5473 0.0209 -0.0491 0.0425 8.2866 0.0083 0.0015 -0.0433 -0.0818 -0.0576 4.4795 0.1019 4.0379 4.0379 5.0750 -0.0639 -0.0621 0.0425 8.1641 0.0043 0.0004 -0.0591 -0.1227 -0.0677 4.5000 0.0181 4.0002 4.0065 4.0065 -0.1402 -0.0735 0.0425 8.0652 0.0008 0.0000 -0.0735 0.0000 0.0000 RADIUS: 4.50 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) = 0.019085 TOTAL WEIGHT (Kg) = 0.008656 TOTAL VOLUME (IN**3) = 0.310926 TOTAL PROJECTED AREA (IN**2) = 6.7051 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000213 MOMENT OF INERTIA (Kg-M**2) = 0.000024 STATIC MOMENT, ONE SIDE (IN-LB) = 0.016006 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 = 129.925 INNER LIMIT (NORMALIZED BY RADIUS) = 0.056 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5447.18 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