5.25x6.25E (525x625E.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 1.0806 0.0000 0.0000 0.2500 0.0000 0.1343 0.0000 0.0672 0.0000 0.0750 0.0000 0.0000 0.0660 0.4794 1.5705 0.0108 -0.1978 0.2467 0.0087 0.1322 1.4871 0.0634 0.0810 0.0817 0.0060 -0.0172 0.1320 0.4595 2.0360 0.0836 -0.3774 0.2433 0.0323 0.1302 5.7533 0.0598 0.0831 0.0992 0.0137 -0.0090 0.1980 0.4453 2.4772 0.2725 -0.4505 0.2402 0.0666 0.1282 12.3560 0.0571 0.0814 0.1220 0.0223 0.0036 0.2640 0.4415 2.8939 0.6203 -0.3294 0.2373 0.1077 0.1264 20.5041 0.0558 0.0762 0.1487 0.0311 0.0194 0.3300 0.4505 3.2863 1.1515 0.0488 0.2348 0.1519 0.1246 29.0448 0.0561 0.0688 0.1791 0.0398 0.0373 0.3960 0.4707 3.6543 1.8620 0.7117 0.2329 0.1955 0.1230 36.8091 0.0579 0.0604 0.2114 0.0479 0.0562 0.4620 0.4973 3.9979 2.7075 1.6330 0.2317 0.2346 0.1214 43.0062 0.0604 0.0520 0.2428 0.0550 0.0750 0.5280 0.5237 4.3171 3.5938 2.7145 0.2312 0.2656 0.1199 47.2892 0.0628 0.0441 0.2695 0.0605 0.0920 0.5940 0.5432 4.6120 4.3769 3.7323 0.2317 0.2847 0.1185 49.5459 0.0644 0.0372 0.2868 0.0641 0.1055 0.6600 0.5504 4.8824 4.8802 4.4591 0.2332 0.2881 0.1172 49.6440 0.0645 0.0318 0.2898 0.0646 0.1128 0.7257 0.5474 5.1275 5.1275 4.8853 0.2352 0.2800 0.1160 48.3532 0.0635 0.0277 0.2818 0.0629 0.1142 0.7870 0.5425 5.3341 5.3341 5.2190 0.2366 0.2713 0.1150 47.1700 0.0624 0.0245 0.2732 0.0618 0.1135 0.8479 0.5371 5.5189 5.5189 5.4893 0.2376 0.2615 0.1140 46.0103 0.0612 0.0222 0.2635 0.0609 0.1107 0.9089 0.5314 5.6829 5.6829 5.6986 0.2383 0.2506 0.1130 44.8606 0.0600 0.0207 0.2527 0.0602 0.1060 0.9698 0.5252 5.8261 5.8261 5.8484 0.2385 0.2386 0.1120 43.7142 0.0588 0.0199 0.2408 0.0598 0.0994 1.0308 0.5187 5.9485 5.9485 5.9684 0.2384 0.2257 0.1110 42.5661 0.0576 0.0193 0.2280 0.0592 0.0920 1.0917 0.5117 6.0501 6.0501 6.0682 0.2379 0.2130 0.1100 41.4118 0.0563 0.0186 0.2154 0.0586 0.0847 1.1527 0.5044 6.1309 6.1309 6.1479 0.2371 0.2006 0.1090 40.2479 0.0550 0.0179 0.2031 0.0579 0.0777 1.2137 0.4966 6.1909 6.1909 6.2067 0.2359 0.1883 0.1080 39.0715 0.0536 0.0172 0.1910 0.0570 0.0710 1.2746 0.4885 6.2301 6.2301 6.2454 0.2343 0.1764 0.1070 37.8801 0.0523 0.0165 0.1791 0.0560 0.0647 1.3356 0.4799 6.2485 6.2485 6.2635 0.2324 0.1646 0.1060 36.6716 0.0509 0.0158 0.1675 0.0550 0.0586 1.3965 0.4710 6.2500 6.2500 6.2651 0.2301 0.1531 0.1050 35.4615 0.0494 0.0151 0.1561 0.0539 0.0527 1.4575 0.4616 6.2500 6.2500 6.2656 0.2276 0.1418 0.1040 34.3132 0.0480 0.0144 0.1450 0.0529 0.0469 1.5184 0.4519 6.2500 6.2500 6.2665 0.2246 0.1307 0.1030 33.2285 0.0465 0.0136 0.1341 0.0519 0.0411 1.5794 0.4417 6.2500 6.2500 6.2648 0.2214 0.1198 0.1020 32.2031 0.0451 0.0130 0.1235 0.0507 0.0348 1.6404 0.4312 6.2500 6.2500 6.2593 0.2178 0.1088 0.1010 31.2328 0.0436 0.0125 0.1131 0.0490 0.0280 1.7013 0.4203 6.2500 6.2500 6.2493 0.2139 0.0980 0.1000 30.3139 0.0420 0.0120 0.1029 0.0472 0.0209 1.7623 0.4089 6.2500 6.2500 6.2336 0.2097 0.0874 0.0990 29.4427 0.0405 0.0116 0.0930 0.0450 0.0136 1.8232 0.3972 6.2500 6.2500 6.2139 0.2052 0.0769 0.0980 28.6161 0.0389 0.0112 0.0833 0.0430 0.0064 1.8842 0.3851 6.2500 6.2500 6.1924 0.2003 0.0668 0.0970 27.8310 0.0374 0.0107 0.0739 0.0410 -0.0006 1.9451 0.3725 6.2500 6.2500 6.1710 0.1952 0.0570 0.0960 27.0846 0.0358 0.0102 0.0647 0.0391 -0.0072 2.0061 0.3596 6.2500 6.2500 6.1517 0.1898 0.0477 0.0950 26.3744 0.0342 0.0097 0.0558 0.0374 -0.0134 2.0671 0.3463 6.2500 6.2500 6.1364 0.1841 0.0387 0.0940 25.6981 0.0326 0.0091 0.0471 0.0359 -0.0190 2.1280 0.3326 6.2500 6.2500 6.1261 0.1781 0.0302 0.0930 25.0533 0.0309 0.0084 0.0387 0.0347 -0.0241 2.1890 0.3185 6.2500 6.2500 6.1221 0.1719 0.0222 0.0920 24.4382 0.0293 0.0077 0.0305 0.0337 -0.0286 2.2499 0.3039 6.2500 6.2500 6.1230 0.1653 0.0145 0.0910 23.8508 0.0277 0.0070 0.0226 0.0328 -0.0327 2.3109 0.2890 6.2500 6.2500 6.1239 0.1585 0.0071 0.0900 23.2895 0.0260 0.0062 0.0149 0.0320 -0.0366 2.3718 0.2737 6.2500 6.2500 6.1255 0.1515 0.0000 0.0890 22.7526 0.0244 0.0056 0.0075 0.0311 -0.0404 2.4328 0.2580 6.2500 6.2500 6.1277 0.1442 -0.0069 0.0880 22.2386 0.0227 0.0049 0.0003 0.0302 -0.0440 2.4913 0.2411 6.2500 6.2500 6.1304 0.1355 -0.0138 0.0870 21.7660 0.0210 0.0042 -0.0070 0.0286 -0.0476 2.5070 0.2335 6.2500 6.2500 6.1313 0.1305 -0.0167 0.0868 21.6419 0.0203 0.0040 -0.0100 0.0267 -0.0492 2.5203 0.2256 6.2500 6.2500 6.1321 0.1247 -0.0197 0.0866 21.5385 0.0195 0.0037 -0.0132 0.0244 -0.0509 2.5335 0.2159 6.2500 6.2500 6.1339 0.1173 -0.0232 0.0864 21.4361 0.0186 0.0034 -0.0171 0.0212 -0.0530 2.5468 0.2042 6.2500 6.2500 6.1426 0.1080 -0.0275 0.0861 21.3346 0.0176 0.0030 -0.0217 0.0170 -0.0556 2.5600 0.1900 6.2500 6.2500 6.1552 0.0964 -0.0327 0.0859 21.2339 0.0163 0.0026 -0.0272 0.0115 -0.0587 2.5733 0.1723 6.2500 6.2500 6.1747 0.0816 -0.0390 0.0857 21.1342 0.0148 0.0022 -0.0340 0.0044 -0.0626 2.5866 0.1492 6.2500 6.2500 6.2081 0.0617 -0.0472 0.0855 21.0354 0.0128 0.0016 -0.0429 -0.0055 -0.0676 2.5998 0.1139 6.2500 6.2500 6.2870 0.0304 -0.0597 0.0853 20.9374 0.0097 0.0010 -0.0564 -0.0214 -0.0754 2.6131 0.0595 6.2500 6.2500 6.5973 -0.0189 -0.0789 0.0850 20.8404 0.0051 0.0003 -0.0772 -0.0468 -0.0874 2.6250 0.0103 6.2500 6.2532 6.2531 -0.0634 -0.0960 0.0849 20.7633 0.0009 0.0000 -0.0960 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) = 0.008370 TOTAL WEIGHT (Kg) = 0.003796 TOTAL VOLUME (IN**3) = 0.136351 TOTAL PROJECTED AREA (IN**2) = 1.8384 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000019 MOMENT OF INERTIA (Kg-M**2) = 0.000002 STATIC MOMENT, ONE SIDE (IN-LB) = 0.002914 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) = 28785.08 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