5x4.5E (5x45E.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 4.6000 0.0000 0.0000 0.2500 0.0000 0.2368 0.0000 0.1184 0.0000 0.0850 0.0000 0.0000 0.0660 0.4792 4.6000 0.0121 -0.1811 0.2469 0.0074 0.2214 1.6717 0.1061 0.0816 0.0900 0.0067 -0.0106 0.1320 0.4597 4.6000 0.0940 -0.3514 0.2442 0.0273 0.2070 6.4656 0.0951 0.0861 0.1036 0.0152 -0.0087 0.1980 0.4479 4.6000 0.3064 -0.4438 0.2421 0.0565 0.1936 13.8343 0.0867 0.0895 0.1220 0.0242 -0.0048 0.2640 0.4498 4.6000 0.6944 -0.2880 0.2407 0.0916 0.1812 22.7149 0.0815 0.0851 0.1414 0.0333 0.0031 0.3300 0.4680 4.6000 1.2773 0.2130 0.2403 0.1293 0.1698 31.6348 0.0795 0.0760 0.1627 0.0418 0.0139 0.3960 0.4999 4.6000 2.0335 1.0802 0.2409 0.1668 0.1594 39.2588 0.0797 0.0648 0.1862 0.0491 0.0264 0.4620 0.5392 4.6000 2.8873 2.1866 0.2427 0.2008 0.1499 44.8463 0.0808 0.0533 0.2105 0.0547 0.0398 0.5280 0.5784 4.6000 3.7080 3.2968 0.2457 0.2282 0.1413 48.1811 0.0817 0.0431 0.2327 0.0583 0.0530 0.5940 0.6108 4.6000 4.3308 4.1594 0.2502 0.2461 0.1336 49.2456 0.0816 0.0354 0.2486 0.0594 0.0646 0.6600 0.6317 4.6000 4.5976 4.5458 0.2561 0.2512 0.1267 47.9506 0.0801 0.0318 0.2534 0.0568 0.0717 0.7255 0.6436 4.6000 4.6000 4.5611 0.2624 0.2472 0.1208 45.2590 0.0777 0.0316 0.2498 0.0509 0.0739 0.7829 0.6521 4.6000 4.6000 4.5707 0.2670 0.2431 0.1162 43.0814 0.0758 0.0314 0.2461 0.0457 0.0752 0.8397 0.6587 4.6000 4.6000 4.5790 0.2707 0.2387 0.1122 41.0835 0.0739 0.0312 0.2421 0.0411 0.0765 0.8966 0.6636 4.6000 4.6000 4.5856 0.2736 0.2338 0.1088 39.2336 0.0722 0.0309 0.2376 0.0366 0.0775 0.9534 0.6670 4.6000 4.6000 4.5902 0.2756 0.2285 0.1059 37.5191 0.0707 0.0307 0.2328 0.0324 0.0780 1.0103 0.6688 4.6000 4.6000 4.5928 0.2769 0.2228 0.1036 35.9286 0.0693 0.0305 0.2277 0.0284 0.0780 1.0672 0.6691 4.6000 4.6000 4.5934 0.2774 0.2166 0.1018 34.4513 0.0681 0.0302 0.2222 0.0245 0.0776 1.1240 0.6679 4.6000 4.6000 4.5918 0.2771 0.2101 0.1005 33.0772 0.0671 0.0301 0.2165 0.0208 0.0767 1.1809 0.6654 4.6000 4.6000 4.5883 0.2762 0.2033 0.0996 31.7974 0.0663 0.0299 0.2105 0.0172 0.0753 1.2378 0.6616 4.6000 4.6000 4.5841 0.2746 0.1962 0.0988 30.6036 0.0654 0.0296 0.2043 0.0137 0.0736 1.2946 0.6565 4.6000 4.6000 4.5796 0.2724 0.1889 0.0980 29.4883 0.0643 0.0293 0.1978 0.0103 0.0715 1.3515 0.6503 4.6000 4.6000 4.5747 0.2695 0.1814 0.0972 28.4449 0.0632 0.0289 0.1911 0.0069 0.0691 1.4083 0.6429 4.6000 4.6000 4.5696 0.2661 0.1738 0.0964 27.4672 0.0620 0.0283 0.1843 0.0036 0.0664 1.4652 0.6344 4.6000 4.6000 4.5644 0.2620 0.1661 0.0956 26.5497 0.0606 0.0277 0.1774 0.0003 0.0634 1.5221 0.6250 4.6000 4.6000 4.5590 0.2575 0.1584 0.0948 25.6875 0.0592 0.0271 0.1703 -0.0029 0.0603 1.5789 0.6146 4.6000 4.6000 4.5534 0.2524 0.1506 0.0940 24.8760 0.0578 0.0263 0.1631 -0.0060 0.0570 1.6358 0.6033 4.6000 4.6000 4.5478 0.2469 0.1429 0.0932 24.1113 0.0562 0.0255 0.1559 -0.0091 0.0535 1.6927 0.5912 4.6000 4.6000 4.5423 0.2409 0.1351 0.0924 23.3896 0.0546 0.0246 0.1485 -0.0121 0.0499 1.7495 0.5784 4.6000 4.6000 4.5371 0.2345 0.1273 0.0916 22.7076 0.0530 0.0237 0.1412 -0.0150 0.0463 1.8064 0.5648 4.6000 4.6000 4.5314 0.2276 0.1196 0.0908 22.0624 0.0513 0.0227 0.1338 -0.0178 0.0425 1.8632 0.5507 4.6000 4.6000 4.5247 0.2204 0.1120 0.0900 21.4511 0.0495 0.0216 0.1264 -0.0206 0.0385 1.9201 0.5359 4.6000 4.6000 4.5168 0.2129 0.1046 0.0891 20.8713 0.0478 0.0205 0.1189 -0.0232 0.0345 1.9770 0.5206 4.6000 4.6000 4.5077 0.2050 0.0972 0.0883 20.3207 0.0460 0.0194 0.1115 -0.0259 0.0304 2.0338 0.5049 4.6000 4.6000 4.4973 0.1969 0.0901 0.0875 19.7972 0.0442 0.0183 0.1040 -0.0284 0.0263 2.0907 0.4888 4.6000 4.6000 4.4856 0.1884 0.0831 0.0867 19.2991 0.0424 0.0172 0.0966 -0.0309 0.0222 2.1476 0.4723 4.6000 4.6000 4.4721 0.1798 0.0764 0.0859 18.8245 0.0406 0.0160 0.0893 -0.0333 0.0181 2.2044 0.4556 4.6000 4.6000 4.4558 0.1709 0.0698 0.0851 18.3720 0.0388 0.0149 0.0822 -0.0357 0.0141 2.2613 0.4386 4.6000 4.6000 4.4373 0.1618 0.0635 0.0843 17.9399 0.0370 0.0138 0.0752 -0.0380 0.0102 2.3181 0.4216 4.6000 4.6000 4.4163 0.1526 0.0575 0.0835 17.5271 0.0352 0.0127 0.0683 -0.0403 0.0064 2.3727 0.3959 4.6000 4.6000 4.3936 0.1349 0.0493 0.0828 17.1480 0.0328 0.0112 0.0591 -0.0471 0.0013 2.3876 0.3841 4.6000 4.6000 4.3869 0.1255 0.0457 0.0825 17.0470 0.0317 0.0105 0.0551 -0.0512 -0.0008 2.4003 0.3720 4.6000 4.6000 4.3840 0.1154 0.0421 0.0824 16.9625 0.0306 0.0098 0.0511 -0.0559 -0.0030 2.4129 0.3572 4.6000 4.6000 4.3846 0.1028 0.0377 0.0822 16.8788 0.0294 0.0091 0.0463 -0.0620 -0.0056 2.4255 0.3385 4.6000 4.6000 4.3882 0.0865 0.0323 0.0820 16.7959 0.0278 0.0081 0.0403 -0.0701 -0.0089 2.4381 0.3130 4.6000 4.6000 4.3984 0.0636 0.0249 0.0818 16.7138 0.0256 0.0070 0.0323 -0.0816 -0.0133 2.4508 0.2658 4.6000 4.6000 4.4339 0.0199 0.0114 0.0816 16.6324 0.0217 0.0050 0.0176 -0.1041 -0.0212 2.4634 0.2023 4.6000 4.6000 4.5172 -0.0395 -0.0066 0.0815 16.5518 0.0165 0.0030 -0.0019 -0.1350 -0.0317 2.4760 0.1388 4.6000 4.6000 4.6846 -0.0989 -0.0244 0.0813 16.4720 0.0113 0.0014 -0.0212 -0.1657 -0.0421 2.4886 0.0754 4.6000 4.6000 5.1452 -0.1583 -0.0420 0.0811 16.3929 0.0061 0.0004 -0.0403 -0.1963 -0.0522 2.5000 0.0183 4.6000 4.6023 4.6023 -0.2118 -0.0577 0.0809 16.3302 0.0015 0.0000 -0.0577 0.0000 0.0000 RADIUS: 2.50 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.66 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.010745 TOTAL WEIGHT (Kg) = 0.004873 TOTAL VOLUME (IN**3) = 0.175052 TOTAL PROJECTED AREA (IN**2) = 2.3684 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000033 MOMENT OF INERTIA (Kg-M**2) = 0.000004 STATIC MOMENT, ONE SIDE (IN-LB) = 0.004543 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 = 156.015 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 30105.35 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