10x4.5MR (10x45MR.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 -7.4918 0.0000 0.0000 0.3250 0.0000 0.4755 0.0000 0.3091 0.0000 0.1000 0.0000 0.0000 0.0800 0.6388 -5.8705 0.0056 -0.2187 0.3211 0.0074 0.4265 0.6368 0.2725 0.1317 0.1049 0.0006 -0.0159 0.1600 0.6233 -4.3670 0.0437 -0.4178 0.3175 0.0277 0.3818 2.4865 0.2380 0.1298 0.1183 0.0051 -0.0043 0.2400 0.6070 -2.9811 0.1447 -0.5619 0.3147 0.0579 0.3412 5.4816 0.2071 0.1269 0.1382 0.0115 0.0127 0.3200 0.5940 -1.7129 0.3383 -0.5527 0.3129 0.0948 0.3046 9.5511 0.1809 0.1179 0.1619 0.0198 0.0346 0.4000 0.5883 -0.5624 0.6463 -0.3214 0.3124 0.1357 0.2717 14.4211 0.1598 0.1049 0.1881 0.0289 0.0592 0.4800 0.5930 0.4703 1.0772 0.1648 0.3136 0.1777 0.2423 19.6550 0.1437 0.0904 0.2156 0.0381 0.0844 0.5600 0.6101 1.3854 1.6192 0.8898 0.3167 0.2179 0.2162 24.7106 0.1319 0.0765 0.2431 0.0467 0.1080 0.6400 0.6400 2.1828 2.2346 1.7451 0.3219 0.2535 0.1932 29.0614 0.1236 0.0648 0.2690 0.0541 0.1282 0.7200 0.6821 2.8625 2.8617 2.5670 0.3295 0.2816 0.1731 32.3160 0.1181 0.0570 0.2913 0.0593 0.1423 0.8000 0.7352 3.4245 3.4244 3.2408 0.3398 0.2996 0.1557 34.2651 0.1145 0.0547 0.3068 0.0598 0.1464 0.8828 0.7944 3.8822 3.8822 3.7396 0.3519 0.3092 0.1403 34.9884 0.1115 0.0566 0.3161 0.0548 0.1431 1.0134 0.8776 4.3480 4.3480 4.2651 0.3689 0.3186 0.1209 34.3265 0.1061 0.0586 0.3256 0.0423 0.1420 1.1469 0.9496 4.5000 4.5000 4.4537 0.3836 0.3209 0.1064 31.9834 0.1010 0.0604 0.3292 0.0255 0.1460 1.2803 1.0085 4.5000 4.5000 4.4762 0.3959 0.3165 0.0964 29.2217 0.0972 0.0619 0.3267 0.0087 0.1501 1.4138 1.0545 4.5000 4.5000 4.4892 0.4057 0.3094 0.0898 26.8658 0.0947 0.0634 0.3214 -0.0054 0.1523 1.5472 1.0877 4.5000 4.5000 4.4959 0.4131 0.3014 0.0858 24.8388 0.0933 0.0647 0.3153 -0.0163 0.1543 1.6807 1.1081 4.5000 4.5000 4.4983 0.4182 0.2924 0.0834 23.0804 0.0924 0.0654 0.3083 -0.0236 0.1561 1.8141 1.1159 4.5000 4.5000 4.4993 0.4211 0.2828 0.0816 21.5434 0.0910 0.0650 0.3006 -0.0274 0.1574 1.9476 1.1112 4.5000 4.5000 4.5006 0.4219 0.2727 0.0799 20.1903 0.0888 0.0634 0.2921 -0.0279 0.1582 2.0810 1.1002 4.5000 4.5000 4.5022 0.4205 0.2620 0.0785 18.9911 0.0864 0.0612 0.2829 -0.0276 0.1578 2.2145 1.0863 4.5000 4.5000 4.5038 0.4172 0.2508 0.0772 17.9220 0.0839 0.0588 0.2731 -0.0276 0.1560 2.3479 1.0696 4.5000 4.5000 4.5054 0.4119 0.2392 0.0761 16.9635 0.0814 0.0563 0.2627 -0.0280 0.1530 2.4814 1.0501 4.5000 4.5000 4.5073 0.4047 0.2272 0.0751 16.0997 0.0789 0.0538 0.2517 -0.0289 0.1489 2.6148 1.0281 4.5000 4.5000 4.5093 0.3958 0.2149 0.0743 15.3176 0.0764 0.0511 0.2403 -0.0303 0.1438 2.7483 1.0035 4.5000 4.5000 4.5115 0.3852 0.2023 0.0736 14.6063 0.0738 0.0483 0.2284 -0.0322 0.1379 2.8817 0.9765 4.5000 4.5000 4.5137 0.3729 0.1895 0.0730 13.9570 0.0713 0.0455 0.2161 -0.0346 0.1312 3.0152 0.9473 4.5000 4.5000 4.5124 0.3591 0.1764 0.0725 13.3619 0.0687 0.0430 0.2035 -0.0384 0.1234 3.1486 0.9158 4.5000 4.5000 4.5057 0.3438 0.1631 0.0722 12.8147 0.0661 0.0406 0.1906 -0.0438 0.1144 3.2821 0.8823 4.5000 4.5000 4.4936 0.3270 0.1496 0.0719 12.3098 0.0635 0.0385 0.1774 -0.0505 0.1047 3.4155 0.8468 4.5000 4.5000 4.4763 0.3089 0.1361 0.0718 11.8427 0.0608 0.0365 0.1640 -0.0579 0.0943 3.5490 0.8094 4.5000 4.5000 4.4545 0.2896 0.1226 0.0717 11.4093 0.0580 0.0344 0.1505 -0.0657 0.0836 3.6824 0.7702 4.5000 4.5000 4.4294 0.2690 0.1092 0.0717 11.0061 0.0552 0.0322 0.1369 -0.0735 0.0728 3.8159 0.7294 4.5000 4.5000 4.4023 0.2474 0.0959 0.0717 10.6301 0.0523 0.0299 0.1232 -0.0811 0.0620 3.9493 0.6869 4.5000 4.5000 4.3753 0.2246 0.0829 0.0719 10.2787 0.0494 0.0274 0.1095 -0.0882 0.0514 4.0828 0.6431 4.5000 4.5000 4.3501 0.2010 0.0701 0.0720 9.9496 0.0463 0.0247 0.0959 -0.0948 0.0412 4.2162 0.5978 4.5000 4.5000 4.3296 0.1764 0.0577 0.0722 9.6407 0.0432 0.0219 0.0824 -0.1010 0.0313 4.3497 0.5513 4.5000 4.5000 4.3162 0.1510 0.0457 0.0725 9.3502 0.0400 0.0189 0.0690 -0.1067 0.0219 4.4831 0.5037 4.5000 4.5000 4.3125 0.1248 0.0340 0.0727 9.0766 0.0366 0.0160 0.0558 -0.1120 0.0130 4.6166 0.4549 4.5000 4.5000 4.3023 0.0979 0.0228 0.0730 8.8184 0.0332 0.0132 0.0423 -0.1171 0.0038 4.7444 0.4067 4.5000 4.5000 4.2507 0.0710 0.0124 0.0733 8.5844 0.0298 0.0107 0.0284 -0.1223 -0.0060 4.7753 0.3912 4.5000 4.5000 4.2296 0.0607 0.0094 0.0734 8.5297 0.0287 0.0099 0.0243 -0.1255 -0.0088 4.8005 0.3757 4.5000 4.5000 4.2107 0.0495 0.0066 0.0734 8.4855 0.0276 0.0092 0.0205 -0.1295 -0.0114 4.8258 0.3575 4.5000 4.5000 4.1965 0.0356 0.0034 0.0735 8.4417 0.0263 0.0083 0.0162 -0.1351 -0.0143 4.8510 0.3359 4.5000 4.5000 4.1840 0.0185 -0.0003 0.0735 8.3984 0.0247 0.0074 0.0113 -0.1423 -0.0174 4.8763 0.3104 4.5000 4.5000 4.1761 -0.0026 -0.0045 0.0736 8.3555 0.0228 0.0063 0.0058 -0.1516 -0.0209 4.9015 0.2797 4.5000 4.5000 4.1782 -0.0287 -0.0094 0.0736 8.3131 0.0206 0.0052 -0.0005 -0.1636 -0.0247 4.9268 0.2416 4.5000 4.5000 4.2047 -0.0623 -0.0154 0.0737 8.2711 0.0178 0.0039 -0.0080 -0.1795 -0.0291 4.9520 0.1902 4.5000 4.5000 4.3025 -0.1090 -0.0231 0.0737 8.2295 0.0140 0.0024 -0.0176 -0.2022 -0.0345 4.9773 0.1050 4.5000 4.5000 4.8338 -0.1891 -0.0356 0.0738 8.1883 0.0077 0.0008 -0.0327 -0.2424 -0.0424 5.0000 0.0155 4.5000 4.5023 4.5023 -0.2739 -0.0485 0.0738 8.1556 0.0011 0.0000 -0.0485 0.0000 0.0000 RADIUS: 5.00 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.80 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.031540 TOTAL WEIGHT (Kg) = 0.014304 TOTAL VOLUME (IN**3) = 0.513823 TOTAL PROJECTED AREA (IN**2) = 7.6240 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000386 MOMENT OF INERTIA (Kg-M**2) = 0.000044 STATIC MOMENT, ONE SIDE (IN-LB) = 0.027706 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 = 99.710 INNER LIMIT (NORMALIZED BY RADIUS) = 0.065 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 9461.90 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.85, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.65, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412