5.25x4.75E (525x475E.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 0.1343 0.0000 0.0672 0.0000 0.0750 0.0000 0.0000 0.0660 0.4787 4.7500 0.0114 -0.1979 0.2467 0.0088 0.1322 1.5769 0.0633 0.0811 0.0817 0.0064 -0.0176 0.1320 0.4572 4.7500 0.0887 -0.3786 0.2433 0.0324 0.1302 6.1071 0.0595 0.0835 0.0992 0.0151 -0.0102 0.1980 0.4413 4.7500 0.2901 -0.4502 0.2402 0.0667 0.1282 13.1260 0.0566 0.0816 0.1217 0.0248 0.0014 0.2640 0.4369 4.7500 0.6622 -0.3191 0.2373 0.1078 0.1264 21.7618 0.0552 0.0761 0.1484 0.0349 0.0162 0.3300 0.4465 4.7500 1.2312 0.0833 0.2348 0.1521 0.1246 30.7006 0.0557 0.0685 0.1786 0.0445 0.0333 0.3960 0.4683 4.7500 1.9876 0.7848 0.2329 0.1957 0.1230 38.6193 0.0576 0.0599 0.2110 0.0530 0.0519 0.4620 0.4966 4.7500 2.8688 1.7458 0.2317 0.2348 0.1214 44.6626 0.0603 0.0515 0.2425 0.0598 0.0708 0.5280 0.5239 4.7500 3.7473 2.8344 0.2312 0.2657 0.1199 48.4816 0.0628 0.0437 0.2693 0.0641 0.0889 0.5940 0.5435 4.7500 4.4400 3.7816 0.2317 0.2847 0.1185 49.9501 0.0644 0.0371 0.2867 0.0653 0.1044 0.6600 0.5504 4.7500 4.7472 4.3306 0.2332 0.2880 0.1172 48.8613 0.0645 0.0318 0.2898 0.0623 0.1152 0.7257 0.5474 4.7500 4.7500 4.5126 0.2352 0.2798 0.1160 46.1695 0.0635 0.0277 0.2818 0.0568 0.1208 0.7870 0.5425 4.7500 4.7500 4.6312 0.2366 0.2709 0.1150 43.8501 0.0624 0.0245 0.2732 0.0530 0.1236 0.8479 0.5371 4.7500 4.7500 4.7066 0.2376 0.2610 0.1140 41.7197 0.0612 0.0222 0.2635 0.0502 0.1238 0.9089 0.5314 4.7500 4.7500 4.7443 0.2383 0.2499 0.1130 39.7532 0.0600 0.0207 0.2527 0.0481 0.1217 0.9698 0.5252 4.7500 4.7500 4.7492 0.2385 0.2378 0.1120 37.9366 0.0588 0.0199 0.2408 0.0467 0.1173 1.0308 0.5187 4.7500 4.7500 4.7469 0.2384 0.2247 0.1110 36.2566 0.0576 0.0193 0.2280 0.0456 0.1114 1.0917 0.5117 4.7500 4.7500 4.7454 0.2379 0.2118 0.1100 34.7010 0.0563 0.0186 0.2154 0.0448 0.1053 1.1527 0.5044 4.7500 4.7500 4.7449 0.2371 0.1991 0.1090 33.2585 0.0550 0.0179 0.2031 0.0442 0.0989 1.2137 0.4966 4.7500 4.7500 4.7447 0.2359 0.1867 0.1080 31.9188 0.0536 0.0172 0.1910 0.0438 0.0925 1.2746 0.4885 4.7500 4.7500 4.7450 0.2343 0.1745 0.1070 30.6726 0.0523 0.0165 0.1791 0.0434 0.0860 1.3356 0.4799 4.7500 4.7500 4.7457 0.2324 0.1626 0.1060 29.5116 0.0509 0.0158 0.1675 0.0432 0.0794 1.3965 0.4710 4.7500 4.7500 4.7468 0.2301 0.1509 0.1050 28.4282 0.0494 0.0151 0.1561 0.0430 0.0728 1.4575 0.4616 4.7500 4.7500 4.7482 0.2276 0.1395 0.1040 27.4154 0.0480 0.0144 0.1450 0.0428 0.0662 1.5184 0.4519 4.7500 4.7500 4.7498 0.2246 0.1284 0.1030 26.4673 0.0465 0.0136 0.1341 0.0426 0.0596 1.5794 0.4417 4.7500 4.7500 4.7494 0.2214 0.1173 0.1020 25.5783 0.0451 0.0130 0.1235 0.0420 0.0526 1.6404 0.4312 4.7500 4.7500 4.7461 0.2178 0.1064 0.1010 24.7435 0.0436 0.0125 0.1131 0.0409 0.0451 1.7013 0.4203 4.7500 4.7500 4.7389 0.2139 0.0956 0.1000 23.9582 0.0420 0.0120 0.1029 0.0395 0.0373 1.7623 0.4089 4.7500 4.7500 4.7265 0.2097 0.0850 0.0990 23.2186 0.0405 0.0116 0.0930 0.0379 0.0294 1.8232 0.3972 4.7500 4.7500 4.7102 0.2052 0.0746 0.0980 22.5210 0.0389 0.0112 0.0834 0.0362 0.0216 1.8842 0.3851 4.7500 4.7500 4.6920 0.2003 0.0646 0.0970 21.8620 0.0374 0.0107 0.0740 0.0346 0.0140 1.9451 0.3725 4.7500 4.7500 4.6735 0.1952 0.0549 0.0960 21.2388 0.0358 0.0102 0.0648 0.0331 0.0067 2.0061 0.3596 4.7500 4.7500 4.6566 0.1898 0.0456 0.0950 20.6486 0.0342 0.0097 0.0559 0.0318 0.0000 2.0671 0.3463 4.7500 4.7500 4.6427 0.1841 0.0368 0.0940 20.0891 0.0326 0.0091 0.0472 0.0307 -0.0063 2.1280 0.3326 4.7500 4.7500 4.6334 0.1781 0.0284 0.0930 19.5578 0.0309 0.0084 0.0388 0.0299 -0.0121 2.1890 0.3185 4.7500 4.7500 4.6296 0.1719 0.0204 0.0920 19.0530 0.0293 0.0077 0.0306 0.0292 -0.0173 2.2499 0.3039 4.7500 4.7500 4.6288 0.1653 0.0128 0.0910 18.5726 0.0277 0.0070 0.0227 0.0288 -0.0221 2.3109 0.2890 4.7500 4.7500 4.6283 0.1585 0.0054 0.0900 18.1151 0.0260 0.0063 0.0150 0.0283 -0.0267 2.3718 0.2737 4.7500 4.7500 4.6282 0.1515 -0.0016 0.0890 17.6789 0.0244 0.0056 0.0076 0.0278 -0.0312 2.4328 0.2580 4.7500 4.7500 4.6286 0.1442 -0.0084 0.0880 17.2625 0.0227 0.0049 0.0004 0.0272 -0.0355 2.4913 0.2405 4.7500 4.7500 4.6296 0.1349 -0.0152 0.0870 16.8807 0.0209 0.0042 -0.0070 0.0256 -0.0398 2.5070 0.2326 4.7500 4.7500 4.6300 0.1295 -0.0179 0.0868 16.7806 0.0202 0.0040 -0.0099 0.0236 -0.0416 2.5203 0.2244 4.7500 4.7500 4.6303 0.1233 -0.0206 0.0866 16.6973 0.0194 0.0037 -0.0129 0.0212 -0.0433 2.5335 0.2146 4.7500 4.7500 4.6353 0.1156 -0.0237 0.0864 16.6147 0.0185 0.0034 -0.0163 0.0178 -0.0453 2.5468 0.2027 4.7500 4.7500 4.6436 0.1060 -0.0274 0.0861 16.5330 0.0175 0.0030 -0.0204 0.0134 -0.0477 2.5600 0.1884 4.7500 4.7500 4.6557 0.0940 -0.0317 0.0859 16.4520 0.0162 0.0026 -0.0252 0.0078 -0.0505 2.5733 0.1706 4.7500 4.7500 4.6741 0.0787 -0.0369 0.0857 16.3718 0.0146 0.0021 -0.0310 0.0004 -0.0539 2.5866 0.1474 4.7500 4.7500 4.7060 0.0582 -0.0436 0.0855 16.2923 0.0126 0.0016 -0.0385 -0.0097 -0.0583 2.5998 0.1116 4.7500 4.7500 4.7846 0.0255 -0.0538 0.0853 16.2136 0.0095 0.0009 -0.0499 -0.0264 -0.0650 2.6131 0.0583 4.7500 4.7500 5.0835 -0.0239 -0.0687 0.0850 16.1357 0.0050 0.0003 -0.0667 -0.0519 -0.0749 2.6250 0.0103 4.7500 4.7524 4.7524 -0.0685 -0.0820 0.0849 16.0738 0.0009 0.0000 -0.0820 0.0000 0.0000 RADIUS: 2.62 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) = 0.008359 TOTAL WEIGHT (Kg) = 0.003791 TOTAL VOLUME (IN**3) = 0.136186 TOTAL PROJECTED AREA (IN**2) = 1.9128 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000019 MOMENT OF INERTIA (Kg-M**2) = 0.000002 STATIC MOMENT, ONE SIDE (IN-LB) = 0.002911 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 = 97.912 INNER LIMIT (NORMALIZED BY RADIUS) = 0.095 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 28772.55 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