9x4.5R-RH (9x45R-RH.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 0.6100 1.9569 0.0000 0.0000 0.3050 0.0000 0.0797 0.0000 0.0486 0.0000 0.1000 0.0000 0.0000 0.0800 0.5905 2.1382 0.0165 -0.1634 0.2952 0.0097 0.0798 1.8843 0.0471 0.1057 0.1070 0.0001 0.0001 0.1600 0.5962 2.3114 0.1214 -0.2781 0.2962 0.0357 0.0799 6.8851 0.0476 0.1172 0.1222 0.0002 0.0002 0.2400 0.6285 2.4762 0.3624 -0.2340 0.3059 0.0733 0.0799 13.5132 0.0502 0.1237 0.1385 0.0004 0.0001 0.3200 0.6859 2.6329 0.7402 0.0102 0.3223 0.1181 0.0800 20.2102 0.0549 0.1254 0.1603 0.0006 -0.0002 0.4000 0.7623 2.7812 1.2213 0.4327 0.3433 0.1660 0.0800 25.9165 0.0610 0.1225 0.1903 0.0006 -0.0007 0.4800 0.8482 2.9214 1.7567 0.9751 0.3669 0.2126 0.0800 30.2190 0.0679 0.1152 0.2256 0.0005 -0.0011 0.5600 0.9330 3.0533 2.2941 1.5647 0.3910 0.2536 0.0800 33.1039 0.0747 0.1046 0.2609 0.0001 -0.0016 0.6400 1.0062 3.1769 2.7824 2.1251 0.4136 0.2848 0.0800 34.6808 0.0805 0.0925 0.2898 -0.0008 -0.0022 0.7200 1.0581 3.2924 3.1700 2.5770 0.4326 0.3019 0.0800 35.0199 0.0847 0.0819 0.3062 -0.0022 -0.0028 0.8000 1.0803 3.3995 3.3984 2.8315 0.4460 0.3006 0.0800 34.0622 0.0864 0.0762 0.3049 -0.0044 -0.0035 0.8819 1.0808 3.5008 3.5008 2.9179 0.4548 0.2863 0.0799 32.2828 0.0864 0.0752 0.2908 -0.0064 -0.0040 0.9971 1.0780 3.6284 3.6284 3.0061 0.4646 0.2671 0.0799 30.0784 0.0861 0.0744 0.2717 -0.0068 -0.0048 1.1141 1.0713 3.7407 3.7407 3.0728 0.4714 0.2484 0.0797 28.1181 0.0854 0.0733 0.2532 -0.0061 -0.0057 1.2312 1.0607 3.8353 3.8353 3.1216 0.4751 0.2308 0.0796 26.3712 0.0844 0.0718 0.2357 -0.0052 -0.0064 1.3483 1.0461 3.9123 3.9123 3.1527 0.4757 0.2140 0.0794 24.7883 0.0831 0.0697 0.2191 -0.0043 -0.0067 1.4653 1.0276 3.9716 3.9716 3.1668 0.4732 0.1981 0.0793 23.3337 0.0814 0.0672 0.2033 -0.0038 -0.0068 1.5824 1.0052 4.0145 4.0145 3.1653 0.4674 0.1831 0.0790 21.9875 0.0795 0.0642 0.1884 -0.0038 -0.0064 1.6995 0.9801 4.0541 4.0541 3.1603 0.4585 0.1692 0.0788 20.7898 0.0772 0.0609 0.1745 -0.0049 -0.0060 1.8166 0.9550 4.0936 4.0936 3.1550 0.4479 0.1564 0.0786 19.7308 0.0751 0.0577 0.1618 -0.0068 -0.0061 1.9336 0.9299 4.1332 4.1332 3.1494 0.4372 0.1446 0.0784 18.7882 0.0729 0.0546 0.1500 -0.0082 -0.0063 2.0507 0.9047 4.1727 4.1727 3.1436 0.4266 0.1338 0.0782 17.9444 0.0707 0.0516 0.1392 -0.0090 -0.0067 2.1678 0.8796 4.2123 4.2123 3.1377 0.4160 0.1239 0.0780 17.1848 0.0686 0.0487 0.1294 -0.0094 -0.0072 2.2848 0.8544 4.2518 4.2518 3.1319 0.4054 0.1149 0.0778 16.4977 0.0664 0.0459 0.1204 -0.0095 -0.0075 2.4019 0.8293 4.2914 4.2914 3.1261 0.3947 0.1066 0.0776 15.8734 0.0643 0.0431 0.1121 -0.0093 -0.0078 2.5190 0.8042 4.3309 4.3309 3.1204 0.3840 0.0991 0.0774 15.3037 0.0622 0.0405 0.1046 -0.0090 -0.0080 2.6360 0.7790 4.3705 4.3705 3.1149 0.3732 0.0923 0.0772 14.7819 0.0601 0.0379 0.0977 -0.0085 -0.0081 2.7531 0.7539 4.4100 4.4100 3.1096 0.3623 0.0861 0.0770 14.3023 0.0581 0.0355 0.0915 -0.0080 -0.0080 2.8702 0.7288 4.4495 4.4495 3.1045 0.3514 0.0805 0.0768 13.8599 0.0560 0.0331 0.0858 -0.0074 -0.0077 2.9872 0.7036 4.4891 4.4891 3.0997 0.3403 0.0753 0.0767 13.4508 0.0539 0.0308 0.0806 -0.0069 -0.0074 3.1043 0.6785 4.5286 4.5286 3.0952 0.3290 0.0706 0.0765 13.0713 0.0519 0.0286 0.0758 -0.0064 -0.0069 3.2214 0.6534 4.5682 4.5682 3.0911 0.3176 0.0663 0.0763 12.7183 0.0499 0.0265 0.0714 -0.0059 -0.0064 3.3384 0.6282 4.6077 4.6077 3.0874 0.3060 0.0623 0.0762 12.3891 0.0479 0.0245 0.0674 -0.0055 -0.0059 3.4555 0.6031 4.6473 4.6473 3.0841 0.2942 0.0586 0.0760 12.0816 0.0459 0.0225 0.0635 -0.0053 -0.0053 3.5726 0.5780 4.6868 4.6868 3.0814 0.2822 0.0551 0.0759 11.7935 0.0439 0.0207 0.0599 -0.0053 -0.0047 3.6897 0.5528 4.7264 4.7264 3.0793 0.2700 0.0517 0.0758 11.5232 0.0419 0.0189 0.0564 -0.0054 -0.0042 3.8067 0.5277 4.7659 4.7659 3.0779 0.2575 0.0485 0.0756 11.2690 0.0399 0.0172 0.0530 -0.0057 -0.0038 3.9238 0.5026 4.8055 4.8055 3.0773 0.2448 0.0452 0.0755 11.0296 0.0380 0.0156 0.0496 -0.0062 -0.0035 4.0409 0.4774 4.8450 4.8450 3.0776 0.2317 0.0419 0.0754 10.8037 0.0360 0.0141 0.0461 -0.0070 -0.0035 4.1579 0.4523 4.8845 4.8845 3.0790 0.2184 0.0385 0.0753 10.5902 0.0341 0.0126 0.0426 -0.0081 -0.0036 4.2701 0.4282 4.9224 4.9224 3.0814 0.2053 0.0352 0.0752 10.3964 0.0322 0.0113 0.0391 -0.0094 -0.0041 4.2977 0.4223 4.9318 4.9318 3.0823 0.2020 0.0343 0.0752 10.3501 0.0317 0.0110 0.0382 -0.0097 -0.0042 4.3205 0.4174 4.9394 4.9395 3.0830 0.1993 0.0336 0.0751 10.3126 0.0314 0.0107 0.0374 -0.0100 -0.0043 4.3432 0.4125 4.9471 4.9471 3.0838 0.1966 0.0329 0.0751 10.2753 0.0310 0.0105 0.0367 -0.0104 -0.0045 4.3659 0.4076 4.9548 4.9548 3.0846 0.1939 0.0321 0.0751 10.2385 0.0306 0.0103 0.0359 -0.0107 -0.0047 4.3886 0.4028 4.9625 4.9625 3.0855 0.1911 0.0314 0.0751 10.2021 0.0302 0.0100 0.0351 -0.0110 -0.0048 4.4114 0.3951 4.9702 4.9705 3.0869 0.1870 0.0304 0.0751 10.1667 0.0297 0.0096 0.0341 -0.0114 -0.0050 4.4341 0.3807 4.9778 4.9795 3.0892 0.1795 0.0288 0.0750 10.1336 0.0286 0.0089 0.0324 -0.0116 -0.0052 4.4568 0.3555 4.9855 4.9903 3.0974 0.1668 0.0263 0.0750 10.1043 0.0267 0.0078 0.0296 -0.0118 -0.0054 4.4795 0.3088 4.9932 5.0056 3.1364 0.1434 0.0219 0.0750 10.0843 0.0232 0.0059 0.0248 -0.0120 -0.0056 4.5000 0.1834 5.0001 5.0422 5.0422 0.0814 0.0108 0.0750 10.1113 0.0138 0.0000 0.0107 0.0000 0.0000 RADIUS: 4.50 PROPELLER RADIUS (IN) HUBRAD: 0.31 HUB RADIUS (IN) HUBTRA: 0.80 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.028855 TOTAL WEIGHT (Kg) = 0.013086 TOTAL VOLUME (IN**3) = 0.470087 TOTAL PROJECTED AREA (IN**2) = 6.4814 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000251 MOMENT OF INERTIA (Kg-M**2) = 0.000028 STATIC MOMENT, ONE SIDE (IN-LB) = 0.021062 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 = 99.247 INNER LIMIT (NORMALIZED BY RADIUS) = 0.068 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 11221.04 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.50, APC16009R (Transition Start, Airfoil 1) AIRFOIL2: 4.00, APC16009R (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.