4.75x4.75E (475x475E.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 4.7500 0.0000 0.0000 0.2500 0.0000 0.2343 0.0000 0.1172 0.0000 0.0750 0.0000 0.0000 0.0660 0.4780 4.7500 0.0105 -0.1981 0.2467 0.0088 0.2177 1.4451 0.1041 0.0806 0.0817 0.0067 -0.0170 0.1320 0.4543 4.7500 0.0816 -0.3812 0.2433 0.0324 0.2024 5.6187 0.0920 0.0817 0.0992 0.0163 -0.0081 0.1980 0.4343 4.7500 0.2684 -0.4645 0.2402 0.0667 0.1885 12.1748 0.0819 0.0787 0.1224 0.0274 0.0056 0.2640 0.4236 4.7500 0.6181 -0.3582 0.2373 0.1078 0.1760 20.4374 0.0745 0.0723 0.1495 0.0392 0.0231 0.3300 0.4252 4.7500 1.1624 0.0095 0.2348 0.1521 0.1648 29.2764 0.0701 0.0640 0.1799 0.0508 0.0430 0.3960 0.4384 4.7500 1.9022 0.6778 0.2329 0.1957 0.1550 37.3978 0.0679 0.0552 0.2120 0.0615 0.0642 0.4620 0.4583 4.7500 2.7857 1.6231 0.2317 0.2348 0.1466 43.8201 0.0672 0.0466 0.2432 0.0703 0.0854 0.5280 0.4785 4.7500 3.6893 2.7262 0.2312 0.2658 0.1395 48.0376 0.0667 0.0389 0.2695 0.0767 0.1050 0.5940 0.4923 4.7500 4.4184 3.7127 0.2317 0.2848 0.1338 49.8125 0.0659 0.0325 0.2868 0.0799 0.1213 0.6600 0.4950 4.7500 4.7470 4.2948 0.2332 0.2881 0.1295 48.8600 0.0641 0.0275 0.2898 0.0786 0.1320 0.7253 0.4897 4.7500 4.7500 4.4860 0.2351 0.2800 0.1265 46.1864 0.0620 0.0237 0.2819 0.0746 0.1368 0.7788 0.4849 4.7500 4.7500 4.5948 0.2364 0.2724 0.1251 44.1496 0.0607 0.0213 0.2744 0.0720 0.1385 0.8315 0.4799 4.7500 4.7500 4.6683 0.2374 0.2640 0.1243 42.2754 0.0596 0.0196 0.2662 0.0700 0.1385 0.8843 0.4745 4.7500 4.7500 4.7129 0.2380 0.2547 0.1234 40.5270 0.0585 0.0182 0.2572 0.0686 0.1367 0.9371 0.4688 4.7500 4.7500 4.7302 0.2384 0.2447 0.1225 38.8951 0.0574 0.0174 0.2473 0.0677 0.1333 0.9898 0.4627 4.7500 4.7500 4.7286 0.2385 0.2338 0.1217 37.3707 0.0563 0.0168 0.2366 0.0671 0.1283 1.0426 0.4564 4.7500 4.7500 4.7269 0.2383 0.2225 0.1208 35.9457 0.0551 0.0163 0.2256 0.0668 0.1227 1.0954 0.4497 4.7500 4.7500 4.7260 0.2379 0.2113 0.1199 34.6121 0.0539 0.0157 0.2147 0.0666 0.1170 1.1481 0.4426 4.7500 4.7500 4.7257 0.2372 0.2004 0.1191 33.3627 0.0527 0.0151 0.2040 0.0665 0.1112 1.2009 0.4353 4.7500 4.7500 4.7259 0.2362 0.1896 0.1182 32.1910 0.0514 0.0145 0.1935 0.0666 0.1053 1.2537 0.4276 4.7500 4.7500 4.7267 0.2349 0.1790 0.1173 31.0907 0.0502 0.0139 0.1832 0.0667 0.0994 1.3064 0.4196 4.7500 4.7500 4.7279 0.2334 0.1686 0.1165 30.0563 0.0489 0.0133 0.1730 0.0669 0.0934 1.3592 0.4112 4.7500 4.7500 4.7296 0.2316 0.1584 0.1156 29.0827 0.0475 0.0127 0.1631 0.0671 0.0875 1.4120 0.4025 4.7500 4.7500 4.7319 0.2295 0.1484 0.1147 28.1651 0.0462 0.0121 0.1533 0.0674 0.0815 1.4647 0.3935 4.7500 4.7500 4.7345 0.2272 0.1387 0.1139 27.2993 0.0448 0.0115 0.1437 0.0676 0.0756 1.5175 0.3842 4.7500 4.7500 4.7375 0.2247 0.1291 0.1130 26.4814 0.0434 0.0109 0.1343 0.0679 0.0696 1.5703 0.3745 4.7500 4.7500 4.7396 0.2219 0.1196 0.1121 25.7078 0.0420 0.0103 0.1251 0.0679 0.0634 1.6230 0.3646 4.7500 4.7500 4.7401 0.2188 0.1102 0.1113 24.9753 0.0406 0.0098 0.1160 0.0677 0.0570 1.6758 0.3542 4.7500 4.7500 4.7392 0.2156 0.1009 0.1104 24.2809 0.0391 0.0094 0.1072 0.0673 0.0504 1.7286 0.3436 4.7500 4.7500 4.7365 0.2121 0.0918 0.1095 23.6220 0.0376 0.0089 0.0985 0.0668 0.0438 1.7813 0.3326 4.7500 4.7500 4.7314 0.2083 0.0828 0.1087 22.9959 0.0361 0.0085 0.0900 0.0662 0.0371 1.8341 0.3213 4.7500 4.7500 4.7215 0.2043 0.0741 0.1078 22.4005 0.0346 0.0081 0.0817 0.0657 0.0306 1.8869 0.3097 4.7500 4.7500 4.7087 0.2001 0.0656 0.1069 21.8337 0.0331 0.0077 0.0736 0.0652 0.0243 1.9396 0.2977 4.7500 4.7500 4.6958 0.1957 0.0574 0.1061 21.2936 0.0316 0.0072 0.0656 0.0647 0.0183 1.9924 0.2854 4.7500 4.7500 4.6840 0.1911 0.0495 0.1052 20.7784 0.0300 0.0067 0.0579 0.0644 0.0125 2.0452 0.2728 4.7500 4.7500 4.6747 0.1862 0.0419 0.1043 20.2865 0.0285 0.0062 0.0503 0.0643 0.0071 2.0979 0.2598 4.7500 4.7500 4.6688 0.1811 0.0346 0.1035 19.8164 0.0269 0.0057 0.0429 0.0642 0.0021 2.1507 0.2465 4.7500 4.7500 4.6673 0.1758 0.0276 0.1026 19.3668 0.0253 0.0051 0.0357 0.0643 -0.0026 2.2035 0.2329 4.7500 4.7500 4.6713 0.1703 0.0209 0.1017 18.9364 0.0237 0.0045 0.0287 0.0645 -0.0070 2.2541 0.2178 4.7500 4.7500 4.6777 0.1632 0.0141 0.1009 18.5404 0.0220 0.0040 0.0215 0.0638 -0.0114 2.2682 0.2108 4.7500 4.7500 4.6796 0.1586 0.0114 0.1007 18.4328 0.0212 0.0037 0.0186 0.0623 -0.0131 2.2802 0.2034 4.7500 4.7500 4.6813 0.1533 0.0087 0.1005 18.3423 0.0204 0.0035 0.0157 0.0603 -0.0149 2.2922 0.1945 4.7500 4.7500 4.6875 0.1466 0.0055 0.1003 18.2527 0.0195 0.0032 0.0122 0.0575 -0.0169 2.3042 0.1838 4.7500 4.7500 4.6999 0.1382 0.0018 0.1001 18.1639 0.0184 0.0028 0.0081 0.0538 -0.0193 2.3162 0.1708 4.7500 4.7500 4.7176 0.1276 -0.0026 0.0999 18.0760 0.0171 0.0024 0.0033 0.0490 -0.0221 2.3282 0.1548 4.7500 4.7500 4.7443 0.1141 -0.0079 0.0997 17.9889 0.0154 0.0020 -0.0025 0.0426 -0.0256 2.3402 0.1339 4.7500 4.7500 4.7897 0.0960 -0.0146 0.0995 17.9026 0.0133 0.0015 -0.0099 0.0338 -0.0299 2.3522 0.1019 4.7500 4.7500 4.8970 0.0673 -0.0246 0.0993 17.8171 0.0101 0.0009 -0.0210 0.0194 -0.0364 2.3642 0.0532 4.7500 4.7500 5.3113 0.0227 -0.0397 0.0991 17.7324 0.0053 0.0003 -0.0378 -0.0034 -0.0462 2.3750 0.0093 4.7500 4.7524 4.7524 -0.0176 -0.0530 0.0989 17.6651 0.0009 0.0000 -0.0530 0.0000 0.0000 RADIUS: 2.38 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) = 0.007319 TOTAL WEIGHT (Kg) = 0.003319 TOTAL VOLUME (IN**3) = 0.119229 TOTAL PROJECTED AREA (IN**2) = 1.5732 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000013 MOMENT OF INERTIA (Kg-M**2) = 0.000001 STATIC MOMENT, ONE SIDE (IN-LB) = 0.002225 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 = 97.930 INNER LIMIT (NORMALIZED BY RADIUS) = 0.105 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 36546.64 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.50, E63 (Transition Start, Airfoil 1) AIRFOIL2: 2.20, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412