8x4.5MR (8x45MR.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 0.6500 -7.5275 0.0000 0.0000 0.3250 0.0000 0.4759 0.0000 0.3094 0.0000 0.0900 0.0000 0.0000 0.0750 0.6364 -5.6338 0.0070 -0.1918 0.3200 0.0066 0.4188 0.8513 0.2665 0.1220 0.0941 0.0007 -0.0180 0.1500 0.6136 -3.9023 0.0547 -0.3702 0.3131 0.0245 0.3676 3.3186 0.2256 0.1222 0.1055 0.0056 -0.0119 0.2250 0.5874 -2.3328 0.1816 -0.5110 0.3052 0.0512 0.3220 7.3191 0.1892 0.1221 0.1221 0.0128 -0.0029 0.3000 0.5639 -0.9254 0.4266 -0.4950 0.2971 0.0836 0.2817 12.7510 0.1588 0.1134 0.1404 0.0215 0.0098 0.3750 0.5490 0.3198 0.8222 -0.2133 0.2895 0.1191 0.2463 19.2369 0.1352 0.0985 0.1598 0.0306 0.0251 0.4500 0.5471 1.4029 1.3837 0.3980 0.2834 0.1552 0.2154 26.0771 0.1179 0.0813 0.1810 0.0391 0.0414 0.5250 0.5595 2.3239 2.0911 1.3343 0.2794 0.1892 0.1889 32.3714 0.1057 0.0648 0.2037 0.0462 0.0571 0.6000 0.5851 3.0828 2.8710 2.4162 0.2782 0.2186 0.1662 37.2909 0.0973 0.0510 0.2262 0.0511 0.0709 0.6750 0.6210 3.6796 3.5953 3.4066 0.2806 0.2408 0.1472 40.2886 0.0914 0.0414 0.2451 0.0533 0.0813 0.7500 0.6647 4.1143 4.1135 4.0692 0.2874 0.2532 0.1314 41.1178 0.0874 0.0377 0.2566 0.0512 0.0852 0.8264 0.7113 4.3905 4.3905 4.3752 0.2969 0.2575 0.1184 40.2153 0.0842 0.0385 0.2613 0.0438 0.0843 0.9276 0.7647 4.5000 4.5000 4.5038 0.3078 0.2590 0.1052 37.6720 0.0805 0.0395 0.2634 0.0299 0.0865 1.0302 0.8094 4.5000 4.5000 4.5150 0.3171 0.2559 0.0959 34.8078 0.0776 0.0404 0.2611 0.0157 0.0892 1.1328 0.8444 4.5000 4.5000 4.5212 0.3245 0.2508 0.0897 32.3035 0.0757 0.0413 0.2571 0.0034 0.0911 1.2353 0.8700 4.5000 4.5000 4.5246 0.3302 0.2450 0.0858 30.1032 0.0747 0.0422 0.2524 -0.0066 0.0932 1.3379 0.8861 4.5000 4.5000 4.5248 0.3342 0.2385 0.0834 28.1602 0.0739 0.0426 0.2470 -0.0137 0.0956 1.4405 0.8928 4.5000 4.5000 4.5246 0.3366 0.2315 0.0817 26.4357 0.0729 0.0425 0.2411 -0.0182 0.0981 1.5431 0.8902 4.5000 4.5000 4.5255 0.3373 0.2240 0.0801 24.8973 0.0713 0.0415 0.2346 -0.0201 0.1004 1.6457 0.8820 4.5000 4.5000 4.5271 0.3365 0.2162 0.0787 23.5185 0.0694 0.0401 0.2277 -0.0208 0.1020 1.7483 0.8717 4.5000 4.5000 4.5286 0.3342 0.2079 0.0774 22.2769 0.0675 0.0387 0.2202 -0.0217 0.1026 1.8509 0.8592 4.5000 4.5000 4.5304 0.3305 0.1992 0.0763 21.1541 0.0656 0.0372 0.2123 -0.0227 0.1021 1.9534 0.8448 4.5000 4.5000 4.5324 0.3254 0.1902 0.0753 20.1346 0.0636 0.0356 0.2040 -0.0240 0.1007 2.0560 0.8284 4.5000 4.5000 4.5347 0.3190 0.1808 0.0745 19.2052 0.0617 0.0339 0.1953 -0.0255 0.0984 2.1586 0.8101 4.5000 4.5000 4.5372 0.3112 0.1712 0.0738 18.3551 0.0598 0.0322 0.1863 -0.0273 0.0954 2.2612 0.7901 4.5000 4.5000 4.5399 0.3023 0.1614 0.0732 17.5747 0.0578 0.0305 0.1770 -0.0294 0.0918 2.3638 0.7683 4.5000 4.5000 4.5416 0.2921 0.1513 0.0727 16.8561 0.0558 0.0288 0.1674 -0.0321 0.0873 2.4664 0.7449 4.5000 4.5000 4.5396 0.2809 0.1409 0.0723 16.1925 0.0538 0.0272 0.1576 -0.0359 0.0818 2.5690 0.7199 4.5000 4.5000 4.5337 0.2685 0.1303 0.0720 15.5778 0.0518 0.0258 0.1475 -0.0405 0.0754 2.6716 0.6934 4.5000 4.5000 4.5240 0.2551 0.1196 0.0718 15.0071 0.0498 0.0245 0.1373 -0.0459 0.0685 2.7741 0.6654 4.5000 4.5000 4.5108 0.2408 0.1089 0.0717 14.4759 0.0477 0.0232 0.1270 -0.0516 0.0611 2.8767 0.6362 4.5000 4.5000 4.4948 0.2256 0.0981 0.0716 13.9803 0.0456 0.0219 0.1166 -0.0574 0.0534 2.9793 0.6056 4.5000 4.5000 4.4769 0.2095 0.0875 0.0716 13.5169 0.0434 0.0205 0.1061 -0.0632 0.0457 3.0819 0.5738 4.5000 4.5000 4.4583 0.1925 0.0769 0.0717 13.0827 0.0411 0.0190 0.0956 -0.0688 0.0380 3.1845 0.5409 4.5000 4.5000 4.4406 0.1748 0.0666 0.0718 12.6751 0.0388 0.0174 0.0851 -0.0740 0.0306 3.2871 0.5069 4.5000 4.5000 4.4253 0.1565 0.0565 0.0720 12.2917 0.0365 0.0157 0.0746 -0.0790 0.0234 3.3897 0.4719 4.5000 4.5000 4.4143 0.1374 0.0468 0.0722 11.9305 0.0341 0.0139 0.0642 -0.0835 0.0165 3.4922 0.4360 4.5000 4.5000 4.4095 0.1178 0.0373 0.0724 11.5897 0.0316 0.0121 0.0539 -0.0878 0.0100 3.5948 0.3992 4.5000 4.5000 4.4034 0.0976 0.0282 0.0727 11.2675 0.0290 0.0102 0.0435 -0.0919 0.0034 3.6974 0.3617 4.5000 4.5000 4.3822 0.0769 0.0195 0.0729 10.9626 0.0264 0.0085 0.0327 -0.0959 -0.0035 3.7957 0.3246 4.5000 4.5000 4.3425 0.0561 0.0113 0.0732 10.6853 0.0238 0.0069 0.0222 -0.0998 -0.0104 3.8202 0.3125 4.5000 4.5000 4.3278 0.0482 0.0088 0.0733 10.6183 0.0229 0.0064 0.0189 -0.1022 -0.0125 3.8404 0.3002 4.5000 4.5000 4.3143 0.0394 0.0064 0.0733 10.5637 0.0220 0.0059 0.0159 -0.1053 -0.0144 3.8606 0.2857 4.5000 4.5000 4.3067 0.0285 0.0035 0.0734 10.5097 0.0210 0.0054 0.0123 -0.1095 -0.0166 3.8808 0.2686 4.5000 4.5000 4.3043 0.0149 0.0003 0.0734 10.4562 0.0197 0.0048 0.0083 -0.1152 -0.0191 3.9010 0.2483 4.5000 4.5000 4.3081 -0.0018 -0.0036 0.0735 10.4032 0.0182 0.0041 0.0036 -0.1225 -0.0218 3.9212 0.2238 4.5000 4.5000 4.3245 -0.0225 -0.0081 0.0735 10.3508 0.0165 0.0033 -0.0019 -0.1318 -0.0249 3.9414 0.1934 4.5000 4.5000 4.3676 -0.0492 -0.0136 0.0736 10.2989 0.0142 0.0025 -0.0084 -0.1443 -0.0286 3.9616 0.1524 4.5000 4.5000 4.4847 -0.0862 -0.0210 0.0736 10.2475 0.0112 0.0016 -0.0171 -0.1621 -0.0332 3.9818 0.0843 4.5000 4.5000 5.0358 -0.1499 -0.0331 0.0737 10.1966 0.0062 0.0005 -0.0310 -0.1936 -0.0403 4.0000 0.0124 4.5000 4.5023 4.5023 -0.2177 -0.0457 0.0737 10.1562 0.0009 0.0000 -0.0457 0.0000 0.0000 RADIUS: 4.00 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.75 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.019095 TOTAL WEIGHT (Kg) = 0.008660 TOTAL VOLUME (IN**3) = 0.311090 TOTAL PROJECTED AREA (IN**2) = 4.8581 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000130 MOMENT OF INERTIA (Kg-M**2) = 0.000015 STATIC MOMENT, ONE SIDE (IN-LB) = 0.011938 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 = 99.596 INNER LIMIT (NORMALIZED BY RADIUS) = 0.081 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 12973.69 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.28, E63 (Transition Start, Airfoil 1) AIRFOIL2: 3.72, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412