5.2x6.0E (52x60E.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 0.0619 0.0000 0.0000 0.2500 0.0000 0.1945 0.0000 0.0973 0.0000 0.0800 0.0000 0.0000 0.0550 0.4812 0.6299 0.0086 -0.1504 0.2462 0.0067 0.1876 1.4191 0.0903 0.0792 0.0845 0.0049 -0.0124 0.1100 0.4605 1.1689 0.0667 -0.2646 0.2407 0.0249 0.1808 5.5128 0.0832 0.0772 0.0951 0.0109 -0.0079 0.1650 0.4433 1.6788 0.2197 -0.2603 0.2344 0.0514 0.1741 11.9647 0.0772 0.0714 0.1094 0.0172 -0.0001 0.2200 0.4352 2.1596 0.5072 -0.0649 0.2277 0.0834 0.1676 20.1488 0.0729 0.0634 0.1271 0.0235 0.0101 0.2750 0.4398 2.6114 0.9580 0.3779 0.2214 0.1181 0.1613 29.0061 0.0709 0.0544 0.1478 0.0297 0.0216 0.3300 0.4569 3.0341 1.5798 1.0924 0.2162 0.1527 0.1551 37.3043 0.0709 0.0456 0.1705 0.0357 0.0334 0.3850 0.4828 3.4277 2.3438 1.9996 0.2125 0.1844 0.1492 44.0951 0.0720 0.0379 0.1935 0.0413 0.0446 0.4400 0.5112 3.7923 3.1700 2.9653 0.2112 0.2102 0.1435 48.9080 0.0734 0.0317 0.2143 0.0464 0.0541 0.4950 0.5359 4.1278 3.9230 3.8400 0.2128 0.2273 0.1381 51.5928 0.0740 0.0275 0.2294 0.0507 0.0604 0.5500 0.5516 4.4342 4.4323 4.4183 0.2180 0.2329 0.1330 52.0573 0.0734 0.0257 0.2345 0.0539 0.0619 0.6055 0.5603 4.7139 4.7139 4.7099 0.2253 0.2303 0.1281 51.0948 0.0718 0.0256 0.2320 0.0557 0.0594 0.6693 0.5693 4.9991 4.9991 5.0075 0.2325 0.2268 0.1229 49.9284 0.0700 0.0254 0.2285 0.0567 0.0566 0.7336 0.5766 5.2468 5.2468 5.2653 0.2386 0.2227 0.1181 48.6999 0.0681 0.0252 0.2246 0.0567 0.0540 0.7979 0.5823 5.4548 5.4548 5.4823 0.2434 0.2181 0.1138 47.4138 0.0662 0.0249 0.2202 0.0558 0.0516 0.8622 0.5863 5.6231 5.6231 5.6574 0.2471 0.2130 0.1099 46.0662 0.0645 0.0246 0.2154 0.0541 0.0494 0.9266 0.5887 5.7516 5.7516 5.7902 0.2497 0.2075 0.1067 44.6531 0.0628 0.0243 0.2102 0.0515 0.0475 0.9909 0.5896 5.8404 5.8404 5.8800 0.2512 0.2017 0.1040 43.1708 0.0613 0.0239 0.2046 0.0482 0.0460 1.0552 0.5891 5.8895 5.8895 5.9268 0.2516 0.1954 0.1019 41.6156 0.0601 0.0237 0.1987 0.0443 0.0447 1.1195 0.5871 5.9017 5.9017 5.9333 0.2511 0.1888 0.1005 39.9977 0.0590 0.0234 0.1925 0.0398 0.0438 1.1838 0.5837 5.9063 5.9063 5.9299 0.2496 0.1819 0.0997 38.4519 0.0582 0.0232 0.1861 0.0352 0.0428 1.2481 0.5790 5.9108 5.9108 5.9263 0.2472 0.1746 0.0990 37.0066 0.0573 0.0230 0.1794 0.0305 0.0412 1.3124 0.5730 5.9154 5.9154 5.9228 0.2439 0.1670 0.0983 35.6539 0.0563 0.0226 0.1725 0.0257 0.0394 1.3767 0.5657 5.9200 5.9200 5.9195 0.2398 0.1592 0.0975 34.3867 0.0552 0.0222 0.1654 0.0209 0.0372 1.4410 0.5573 5.9246 5.9246 5.9163 0.2348 0.1513 0.0968 33.1982 0.0540 0.0217 0.1581 0.0160 0.0347 1.5053 0.5477 5.9291 5.9291 5.9131 0.2291 0.1433 0.0961 32.0822 0.0526 0.0211 0.1508 0.0110 0.0320 1.5697 0.5371 5.9337 5.9337 5.9100 0.2228 0.1352 0.0954 31.0331 0.0512 0.0204 0.1433 0.0060 0.0292 1.6340 0.5254 5.9383 5.9383 5.9072 0.2157 0.1271 0.0947 30.0457 0.0497 0.0197 0.1358 0.0010 0.0263 1.6983 0.5127 5.9429 5.9429 5.9047 0.2080 0.1191 0.0939 29.1151 0.0482 0.0189 0.1282 -0.0039 0.0233 1.7626 0.4991 5.9474 5.9474 5.9026 0.1997 0.1111 0.0932 28.2372 0.0465 0.0180 0.1207 -0.0088 0.0203 1.8269 0.4846 5.9520 5.9520 5.9013 0.1908 0.1033 0.0925 27.4079 0.0448 0.0171 0.1132 -0.0137 0.0173 1.8912 0.4693 5.9566 5.9566 5.9007 0.1814 0.0956 0.0918 26.6236 0.0431 0.0161 0.1057 -0.0185 0.0144 1.9555 0.4531 5.9612 5.9612 5.9012 0.1716 0.0881 0.0911 25.8811 0.0413 0.0151 0.0984 -0.0233 0.0116 2.0198 0.4362 5.9658 5.9658 5.9029 0.1613 0.0808 0.0904 25.1772 0.0394 0.0141 0.0911 -0.0279 0.0089 2.0841 0.4187 5.9703 5.9703 5.9061 0.1507 0.0737 0.0896 24.5094 0.0375 0.0130 0.0840 -0.0325 0.0063 2.1484 0.4004 5.9749 5.9749 5.9111 0.1396 0.0668 0.0889 23.8749 0.0356 0.0119 0.0771 -0.0369 0.0039 2.2128 0.3816 5.9795 5.9795 5.9180 0.1283 0.0603 0.0882 23.2716 0.0337 0.0109 0.0703 -0.0412 0.0017 2.2771 0.3615 5.9841 5.9841 5.9272 0.1160 0.0537 0.0875 22.6973 0.0316 0.0097 0.0635 -0.0458 -0.0006 2.3414 0.3362 5.9886 5.9886 5.9369 0.0992 0.0458 0.0868 22.1501 0.0292 0.0084 0.0550 -0.0524 -0.0037 2.4057 0.3033 5.9932 5.9932 5.9382 0.0755 0.0356 0.0861 21.6282 0.0261 0.0069 0.0439 -0.0622 -0.0086 2.4673 0.2628 5.9976 5.9976 5.9528 0.0443 0.0233 0.0854 21.1502 0.0224 0.0052 0.0301 -0.0761 -0.0153 2.4831 0.2503 5.9987 5.9987 5.9587 0.0347 0.0196 0.0852 21.0310 0.0213 0.0047 0.0260 -0.0803 -0.0173 2.4963 0.2388 5.9997 5.9997 5.9656 0.0256 0.0162 0.0850 20.9330 0.0203 0.0043 0.0222 -0.0844 -0.0192 2.5094 0.2264 6.0006 6.0006 5.9744 0.0153 0.0123 0.0849 20.8358 0.0192 0.0038 0.0179 -0.0893 -0.0214 2.5225 0.2135 6.0015 6.0015 5.9853 0.0034 0.0079 0.0847 20.7395 0.0181 0.0034 0.0131 -0.0955 -0.0240 2.5357 0.2002 6.0025 6.0025 5.9988 -0.0103 0.0029 0.0846 20.6442 0.0169 0.0030 0.0077 -0.1034 -0.0273 2.5488 0.1865 6.0034 6.0034 6.0155 -0.0263 -0.0029 0.0845 20.5496 0.0158 0.0026 0.0014 -0.1134 -0.0313 2.5619 0.1721 6.0043 6.0043 6.0381 -0.0455 -0.0099 0.0843 20.4560 0.0145 0.0022 -0.0060 -0.1263 -0.0363 2.5751 0.1509 6.0053 6.0053 6.0894 -0.0696 -0.0186 0.0842 20.3631 0.0127 0.0017 -0.0152 -0.1409 -0.0420 2.5882 0.1117 6.0062 6.0062 6.2626 -0.1028 -0.0306 0.0840 20.2712 0.0094 0.0010 -0.0282 -0.1566 -0.0483 2.6000 0.0078 6.0070 6.0100 6.0100 -0.1795 -0.0585 0.0839 20.1981 0.0007 0.0000 -0.0585 0.0000 0.0000 RADIUS: 2.60 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.55 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.008142 TOTAL WEIGHT (Kg) = 0.003693 TOTAL VOLUME (IN**3) = 0.132650 TOTAL PROJECTED AREA (IN**2) = 2.0420 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000025 MOMENT OF INERTIA (Kg-M**2) = 0.000003 STATIC MOMENT, ONE SIDE (IN-LB) = 0.003470 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 = 121.144 INNER LIMIT (NORMALIZED BY RADIUS) = 0.096 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 23924.73 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.66, E63 (Transition Start, Airfoil 1) AIRFOIL2: 2.45, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412