6.5x6.5 (65x65.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 -2.8757 0.0000 0.0000 0.3250 0.0000 0.4462 0.0000 0.2900 0.0000 0.1050 0.0000 0.0000 0.0900 0.6208 -1.7844 0.0089 -0.3236 0.3223 0.0067 0.4444 0.8974 0.2759 0.1523 0.1107 0.0105 -0.0324 0.1800 0.5892 -0.7606 0.0698 -0.6311 0.3228 0.0248 0.4392 3.5319 0.2588 0.1488 0.1262 0.0273 -0.0228 0.2700 0.5591 0.1957 0.2331 -0.8449 0.3257 0.0510 0.4306 7.8252 0.2408 0.1435 0.1487 0.0469 -0.0078 0.3600 0.5349 1.0846 0.5448 -0.8807 0.3304 0.0825 0.4185 13.5413 0.2239 0.1363 0.1754 0.0678 0.0107 0.4500 0.5204 1.9059 1.0400 -0.6678 0.3360 0.1165 0.4029 20.1939 0.2097 0.1278 0.2036 0.0887 0.0303 0.5400 0.5173 2.6597 1.7322 -0.1604 0.3421 0.1499 0.3839 27.0455 0.1986 0.1188 0.2302 0.1080 0.0490 0.6300 0.5249 3.3460 2.5967 0.6391 0.3477 0.1800 0.3614 33.2644 0.1897 0.1099 0.2525 0.1242 0.0647 0.7200 0.5403 3.9648 3.5536 1.6532 0.3523 0.2039 0.3354 38.1504 0.1812 0.1016 0.2679 0.1359 0.0752 0.8100 0.5591 4.5161 4.4622 2.7126 0.3552 0.2188 0.3060 41.2434 0.1711 0.0942 0.2740 0.1417 0.0788 0.9000 0.5776 4.9999 5.1396 3.5720 0.3557 0.2218 0.2740 42.2669 0.1582 0.0874 0.2686 0.1403 0.0738 0.9891 0.5922 5.4122 5.5658 4.1748 0.3543 0.2159 0.2458 41.8477 0.1456 0.0805 0.2556 0.1344 0.0637 1.0623 0.6000 5.7018 5.8628 4.6364 0.3528 0.2100 0.2264 41.2944 0.1358 0.0745 0.2450 0.1299 0.0568 1.1347 0.6040 5.9438 6.1107 5.0541 0.3512 0.2034 0.2105 40.6010 0.1271 0.0685 0.2347 0.1258 0.0509 1.2070 0.6042 6.1422 6.3145 5.4260 0.3492 0.1960 0.1979 39.7822 0.1196 0.0627 0.2244 0.1221 0.0461 1.2793 0.6006 6.2970 6.4753 5.7452 0.3470 0.1879 0.1886 38.8539 0.1133 0.0574 0.2142 0.1190 0.0423 1.3516 0.5934 6.4083 6.5942 6.0060 0.3446 0.1790 0.1825 37.8280 0.1083 0.0527 0.2041 0.1166 0.0394 1.4240 0.5825 6.4759 6.6721 6.2037 0.3418 0.1695 0.1796 36.7132 0.1046 0.0487 0.1941 0.1151 0.0373 1.4963 0.5703 6.4999 6.7071 6.3346 0.3388 0.1598 0.1777 35.5044 0.1014 0.0452 0.1842 0.1139 0.0355 1.5686 0.5577 6.5000 6.7177 6.4155 0.3355 0.1502 0.1759 34.2777 0.0981 0.0420 0.1745 0.1128 0.0336 1.6409 0.5448 6.5000 6.7278 6.4695 0.3319 0.1407 0.1740 33.1255 0.0948 0.0392 0.1648 0.1121 0.0313 1.7133 0.5316 6.5000 6.7376 6.4966 0.3279 0.1314 0.1721 32.0420 0.0915 0.0367 0.1552 0.1116 0.0286 1.7856 0.5180 6.5000 6.7470 6.5000 0.3237 0.1223 0.1702 31.0218 0.0882 0.0344 0.1456 0.1113 0.0255 1.8579 0.5041 6.5000 6.7561 6.5002 0.3192 0.1133 0.1683 30.0599 0.0849 0.0322 0.1362 0.1111 0.0223 1.9303 0.4899 6.5000 6.7648 6.5003 0.3143 0.1044 0.1664 29.1517 0.0815 0.0300 0.1269 0.1110 0.0190 2.0026 0.4754 6.5000 6.7731 6.5004 0.3091 0.0957 0.1646 28.2931 0.0782 0.0279 0.1176 0.1107 0.0155 2.0749 0.4606 6.5000 6.7809 6.5004 0.3035 0.0871 0.1627 27.4800 0.0749 0.0259 0.1085 0.1104 0.0119 2.1472 0.4454 6.5000 6.7882 6.5004 0.2976 0.0787 0.1608 26.7090 0.0716 0.0239 0.0995 0.1101 0.0082 2.2196 0.4300 6.5000 6.7949 6.5004 0.2914 0.0704 0.1589 25.9768 0.0683 0.0220 0.0905 0.1096 0.0044 2.2919 0.4142 6.5000 6.8010 6.5004 0.2848 0.0623 0.1570 25.2804 0.0650 0.0202 0.0817 0.1090 0.0005 2.3642 0.3981 6.5000 6.8064 6.5004 0.2778 0.0542 0.1551 24.6169 0.0618 0.0184 0.0729 0.1083 -0.0034 2.4366 0.3817 6.5000 6.8109 6.5003 0.2705 0.0463 0.1533 23.9837 0.0585 0.0167 0.0643 0.1074 -0.0074 2.5089 0.3650 6.5000 6.8145 6.5003 0.2628 0.0385 0.1514 23.3783 0.0553 0.0151 0.0557 0.1063 -0.0114 2.5812 0.3480 6.5000 6.8170 6.5003 0.2547 0.0309 0.1495 22.7985 0.0520 0.0136 0.0472 0.1050 -0.0155 2.6535 0.3307 6.5000 6.8182 6.5002 0.2462 0.0233 0.1476 22.2419 0.0488 0.0121 0.0388 0.1035 -0.0196 2.7259 0.3130 6.5000 6.8179 6.5002 0.2373 0.0159 0.1457 21.7064 0.0456 0.0107 0.0305 0.1018 -0.0237 2.7982 0.2951 6.4910 6.8068 6.4911 0.2280 0.0086 0.1438 21.1642 0.0424 0.0094 0.0223 0.0999 -0.0279 2.8705 0.2768 6.4436 6.7551 6.4438 0.2183 0.0013 0.1420 20.5326 0.0393 0.0082 0.0142 0.0976 -0.0318 2.9428 0.2583 6.3557 6.6601 6.3558 0.2081 -0.0059 0.1401 19.8085 0.0362 0.0071 0.0062 0.0950 -0.0357 3.0152 0.2394 6.2272 6.5212 6.2273 0.1976 -0.0131 0.1382 18.9944 0.0331 0.0060 -0.0018 0.0922 -0.0394 3.0846 0.2210 6.0656 6.3459 6.0657 0.1870 -0.0198 0.1364 18.1299 0.0301 0.0051 -0.0093 0.0891 -0.0430 3.1039 0.2158 6.0140 6.2896 6.0141 0.1840 -0.0217 0.1359 17.8747 0.0293 0.0048 -0.0114 0.0883 -0.0440 3.1203 0.2113 5.9679 6.2393 5.9680 0.1813 -0.0233 0.1354 17.6531 0.0286 0.0046 -0.0132 0.0874 -0.0448 3.1367 0.2050 5.9197 6.1868 5.9201 0.1770 -0.0255 0.1350 17.4278 0.0277 0.0043 -0.0156 0.0857 -0.0460 3.1532 0.1964 5.8694 6.1323 5.8704 0.1704 -0.0283 0.1346 17.1986 0.0264 0.0040 -0.0187 0.0828 -0.0477 3.1696 0.1851 5.8170 6.0755 5.8249 0.1612 -0.0318 0.1342 16.9654 0.0248 0.0035 -0.0228 0.0784 -0.0499 3.1860 0.1703 5.7625 6.0163 5.7922 0.1486 -0.0363 0.1337 16.7278 0.0228 0.0030 -0.0280 0.0723 -0.0527 3.2024 0.1507 5.7059 5.9547 5.7745 0.1313 -0.0420 0.1333 16.4857 0.0201 0.0023 -0.0347 0.0635 -0.0564 3.2188 0.1221 5.6472 5.8907 5.8004 0.1055 -0.0502 0.1329 16.2391 0.0162 0.0015 -0.0441 0.0501 -0.0617 3.2352 0.0675 5.5865 5.8254 6.1217 0.0545 -0.0652 0.1325 15.9911 0.0089 0.0005 -0.0619 0.0231 -0.0718 3.2500 0.0088 5.5300 5.5300 5.5300 -0.0007 -0.0811 0.1321 15.1528 0.0012 0.0000 -0.0811 0.0000 0.0000 RADIUS: 3.25 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.90 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.022805 TOTAL WEIGHT (Kg) = 0.010342 TOTAL VOLUME (IN**3) = 0.371520 TOTAL PROJECTED AREA (IN**2) = 2.6529 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000075 MOMENT OF INERTIA (Kg-M**2) = 0.000008 STATIC MOMENT, ONE SIDE (IN-LB) = 0.010001 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 = 80.280 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 49355.21 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.