6.5x5.0 (65x50.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 5.0000 0.0000 0.0000 0.3250 0.0000 0.4462 0.0000 0.2900 0.0000 0.1150 0.0000 0.0000 0.0900 0.6194 5.0000 0.0103 -0.3066 0.3223 0.0062 0.4444 1.0472 0.2753 0.1527 0.1198 0.0116 -0.0250 0.1800 0.5844 5.0000 0.0814 -0.6007 0.3228 0.0230 0.4392 4.1176 0.2567 0.1496 0.1325 0.0302 -0.0195 0.2700 0.5506 5.0000 0.2719 -0.8021 0.3257 0.0474 0.4306 9.1056 0.2371 0.1444 0.1513 0.0519 -0.0099 0.3600 0.5240 5.0000 0.6361 -0.8187 0.3304 0.0766 0.4185 15.7064 0.2193 0.1368 0.1735 0.0750 0.0026 0.4500 0.5094 5.0000 1.2147 -0.5696 0.3360 0.1079 0.4029 23.2491 0.2053 0.1278 0.1969 0.0978 0.0164 0.5400 0.5086 5.0000 2.0155 -0.0026 0.3421 0.1387 0.3839 30.7121 0.1953 0.1182 0.2189 0.1183 0.0298 0.6300 0.5198 5.0000 2.9843 0.8697 0.3477 0.1662 0.3614 37.0130 0.1878 0.1091 0.2373 0.1346 0.0414 0.7200 0.5382 5.0000 3.9789 1.9272 0.3523 0.1878 0.3354 41.3328 0.1805 0.1009 0.2498 0.1448 0.0501 0.8100 0.5586 5.0000 4.7767 2.9295 0.3552 0.2009 0.3060 43.1849 0.1710 0.0938 0.2545 0.1471 0.0548 0.9000 0.5776 5.0000 5.1384 3.5712 0.3557 0.2027 0.2740 42.2607 0.1583 0.0874 0.2495 0.1402 0.0547 0.9891 0.5929 5.0000 5.1569 3.8584 0.3543 0.1966 0.2458 39.6860 0.1457 0.0803 0.2383 0.1288 0.0525 1.0623 0.6009 5.0000 5.1640 4.0678 0.3528 0.1911 0.2264 37.7275 0.1360 0.0741 0.2292 0.1207 0.0515 1.1347 0.6049 5.0000 5.1683 4.2536 0.3512 0.1852 0.2105 35.9402 0.1273 0.0680 0.2203 0.1139 0.0510 1.2070 0.6051 5.0000 5.1719 4.4188 0.3492 0.1788 0.1979 34.2928 0.1198 0.0622 0.2115 0.1085 0.0508 1.2793 0.6015 5.0000 5.1761 4.5634 0.3470 0.1718 0.1886 32.7792 0.1134 0.0570 0.2028 0.1045 0.0506 1.3516 0.5942 5.0000 5.1824 4.6874 0.3446 0.1641 0.1825 31.3927 0.1084 0.0524 0.1942 0.1020 0.0504 1.4240 0.5832 5.0000 5.1918 4.7907 0.3418 0.1559 0.1796 30.1258 0.1048 0.0485 0.1857 0.1010 0.0500 1.4963 0.5709 5.0000 5.2022 4.8734 0.3388 0.1476 0.1777 28.9572 0.1015 0.0450 0.1773 0.1008 0.0492 1.5686 0.5583 5.0000 5.2123 4.9354 0.3355 0.1395 0.1759 27.8720 0.0982 0.0420 0.1690 0.1009 0.0479 1.6409 0.5453 5.0000 5.2222 4.9767 0.3319 0.1316 0.1740 26.8620 0.0949 0.0392 0.1608 0.1012 0.0461 1.7133 0.5320 5.0000 5.2318 4.9974 0.3279 0.1238 0.1721 25.9202 0.0916 0.0367 0.1526 0.1017 0.0440 1.7856 0.5184 5.0000 5.2412 5.0000 0.3237 0.1162 0.1702 25.0400 0.0882 0.0344 0.1446 0.1023 0.0416 1.8579 0.5045 5.0000 5.2502 5.0001 0.3192 0.1088 0.1683 24.2157 0.0849 0.0322 0.1366 0.1028 0.0390 1.9303 0.4903 5.0000 5.2589 5.0002 0.3143 0.1015 0.1664 23.4422 0.0816 0.0300 0.1287 0.1033 0.0362 2.0026 0.4757 5.0000 5.2673 5.0003 0.3091 0.0943 0.1646 22.7150 0.0783 0.0279 0.1209 0.1038 0.0334 2.0749 0.4608 5.0000 5.2752 5.0003 0.3035 0.0873 0.1627 22.0299 0.0750 0.0259 0.1132 0.1041 0.0304 2.1472 0.4457 5.0000 5.2827 5.0003 0.2976 0.0805 0.1608 21.3831 0.0717 0.0239 0.1056 0.1043 0.0273 2.2196 0.4302 5.0000 5.2896 5.0003 0.2914 0.0737 0.1589 20.7713 0.0684 0.0220 0.0980 0.1043 0.0242 2.2919 0.4144 5.0000 5.2959 5.0002 0.2848 0.0671 0.1570 20.1915 0.0651 0.0202 0.0906 0.1042 0.0210 2.3642 0.3983 5.0000 5.3015 5.0002 0.2778 0.0607 0.1551 19.6408 0.0618 0.0184 0.0832 0.1039 0.0177 2.4366 0.3819 5.0000 5.3063 5.0002 0.2705 0.0543 0.1533 19.1167 0.0585 0.0167 0.0759 0.1034 0.0144 2.5089 0.3651 5.0000 5.3102 5.0002 0.2628 0.0481 0.1514 18.6168 0.0553 0.0151 0.0687 0.1026 0.0111 2.5812 0.3481 5.0000 5.3131 5.0002 0.2547 0.0420 0.1495 18.1387 0.0520 0.0136 0.0616 0.1017 0.0078 2.6535 0.3308 5.0000 5.3147 5.0002 0.2462 0.0360 0.1476 17.6805 0.0488 0.0121 0.0546 0.1005 0.0044 2.7259 0.3131 5.0000 5.3148 5.0001 0.2373 0.0301 0.1457 17.2399 0.0456 0.0107 0.0476 0.0991 0.0010 2.7982 0.2951 5.0000 5.3132 5.0001 0.2280 0.0243 0.1438 16.8149 0.0425 0.0094 0.0407 0.0974 -0.0024 2.8705 0.2769 5.0000 5.3094 5.0001 0.2183 0.0186 0.1420 16.4033 0.0393 0.0082 0.0339 0.0955 -0.0058 2.9428 0.2583 5.0000 5.3031 5.0001 0.2081 0.0131 0.1401 16.0030 0.0362 0.0071 0.0272 0.0933 -0.0092 3.0152 0.2394 4.9965 5.2900 4.9965 0.1976 0.0076 0.1382 15.6013 0.0331 0.0060 0.0206 0.0908 -0.0126 3.0846 0.2210 4.9709 5.2514 4.9710 0.1870 0.0023 0.1364 15.1605 0.0301 0.0051 0.0144 0.0881 -0.0157 3.1039 0.2158 4.9594 5.2354 4.9595 0.1840 0.0009 0.1359 15.0267 0.0293 0.0048 0.0126 0.0873 -0.0166 3.1203 0.2112 4.9482 5.2201 4.9483 0.1813 -0.0004 0.1354 14.9094 0.0286 0.0046 0.0111 0.0865 -0.0174 3.1367 0.2049 4.9355 5.2034 4.9360 0.1768 -0.0021 0.1350 14.7895 0.0277 0.0043 0.0090 0.0847 -0.0184 3.1532 0.1962 4.9215 5.1853 4.9226 0.1701 -0.0043 0.1346 14.6668 0.0264 0.0040 0.0063 0.0818 -0.0199 3.1696 0.1848 4.9061 5.1656 4.9170 0.1607 -0.0073 0.1342 14.5411 0.0248 0.0035 0.0027 0.0774 -0.0218 3.1860 0.1700 4.8893 5.1443 4.9217 0.1480 -0.0110 0.1337 14.4122 0.0227 0.0030 -0.0018 0.0712 -0.0243 3.2024 0.1503 4.8712 5.1213 4.9420 0.1306 -0.0159 0.1333 14.2797 0.0200 0.0023 -0.0078 0.0624 -0.0276 3.2188 0.1217 4.8517 5.0965 5.0061 0.1044 -0.0229 0.1329 14.1438 0.0162 0.0015 -0.0163 0.0488 -0.0324 3.2352 0.0671 4.8307 5.0712 5.3638 0.0531 -0.0361 0.1325 14.0078 0.0089 0.0005 -0.0324 0.0216 -0.0415 3.2500 0.0088 4.8107 4.8108 4.8108 -0.0021 -0.0500 0.1321 13.2564 0.0012 0.0000 -0.0500 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) = 0.022780 TOTAL WEIGHT (Kg) = 0.010331 TOTAL VOLUME (IN**3) = 0.371122 TOTAL PROJECTED AREA (IN**2) = 2.7153 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000075 MOMENT OF INERTIA (Kg-M**2) = 0.000008 STATIC MOMENT, ONE SIDE (IN-LB) = 0.009980 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) = 49280.53 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.