6.5x6.0 (65x60.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 -0.2505 0.0000 0.0000 0.3250 0.0000 0.4462 0.0000 0.2900 0.0000 0.1050 0.0000 0.0000 0.0900 0.6203 0.4771 0.0093 -0.3238 0.3223 0.0062 0.4444 0.9472 0.2757 0.1524 0.1101 0.0107 -0.0332 0.1800 0.5876 1.1596 0.0736 -0.6323 0.3228 0.0228 0.4392 3.7257 0.2581 0.1490 0.1240 0.0282 -0.0257 0.2700 0.5563 1.7972 0.2459 -0.8466 0.3257 0.0471 0.4306 8.2462 0.2395 0.1438 0.1442 0.0485 -0.0136 0.3600 0.5312 2.3897 0.5745 -0.8790 0.3304 0.0761 0.4185 14.2498 0.2223 0.1364 0.1682 0.0701 0.0016 0.4500 0.5166 2.9373 1.0963 -0.6553 0.3360 0.1073 0.4029 21.1927 0.2081 0.1278 0.1934 0.0916 0.0179 0.5400 0.5141 3.4398 1.8229 -0.1271 0.3421 0.1380 0.3839 28.2473 0.1974 0.1187 0.2171 0.1113 0.0335 0.6300 0.5229 3.8973 2.7204 0.6996 0.3477 0.1657 0.3614 34.4987 0.1890 0.1097 0.2369 0.1276 0.0465 0.7200 0.5394 4.3099 3.6899 1.7333 0.3523 0.1875 0.3354 39.2024 0.1809 0.1014 0.2504 0.1388 0.0555 0.8100 0.5589 4.6774 4.5643 2.7804 0.3552 0.2009 0.3060 41.8863 0.1710 0.0941 0.2554 0.1435 0.0588 0.9000 0.5776 4.9999 5.1391 3.5717 0.3557 0.2032 0.2740 42.2646 0.1582 0.0874 0.2500 0.1403 0.0552 0.9891 0.5924 5.2748 5.4295 4.0693 0.3543 0.1974 0.2458 41.1430 0.1456 0.0805 0.2378 0.1326 0.0479 1.0623 0.6003 5.4679 5.6300 4.4469 0.3528 0.1919 0.2264 40.1466 0.1359 0.0744 0.2278 0.1269 0.0429 1.1347 0.6043 5.6292 5.7967 4.7873 0.3512 0.1857 0.2105 39.1143 0.1272 0.0684 0.2181 0.1219 0.0389 1.2070 0.6045 5.7615 5.9337 5.0902 0.3492 0.1788 0.1979 38.0408 0.1196 0.0626 0.2085 0.1176 0.0357 1.2793 0.6010 5.8647 6.0423 5.3512 0.3470 0.1712 0.1886 36.9322 0.1133 0.0573 0.1989 0.1142 0.0332 1.3516 0.5937 5.9389 6.1236 5.5665 0.3446 0.1630 0.1825 35.7935 0.1083 0.0527 0.1895 0.1117 0.0313 1.4240 0.5828 5.9839 6.1786 5.7327 0.3418 0.1541 0.1796 34.6280 0.1047 0.0487 0.1801 0.1103 0.0300 1.4963 0.5705 6.0000 6.2053 5.8475 0.3388 0.1450 0.1777 33.4262 0.1014 0.0451 0.1709 0.1094 0.0287 1.5686 0.5579 6.0000 6.2157 5.9221 0.3355 0.1360 0.1759 32.2377 0.0981 0.0420 0.1618 0.1087 0.0272 1.6409 0.5450 6.0000 6.2257 5.9719 0.3319 0.1272 0.1740 31.1247 0.0948 0.0392 0.1527 0.1083 0.0253 1.7133 0.5317 6.0000 6.2354 5.9968 0.3279 0.1186 0.1721 30.0810 0.0915 0.0367 0.1438 0.1081 0.0230 1.7856 0.5182 6.0000 6.2448 6.0000 0.3237 0.1101 0.1702 29.1008 0.0882 0.0344 0.1349 0.1082 0.0203 1.8579 0.5043 6.0000 6.2538 6.0001 0.3192 0.1018 0.1683 28.1788 0.0849 0.0322 0.1261 0.1082 0.0175 1.9303 0.4901 6.0000 6.2625 6.0003 0.3143 0.0936 0.1664 27.3101 0.0816 0.0300 0.1174 0.1083 0.0146 2.0026 0.4755 6.0000 6.2708 6.0004 0.3091 0.0856 0.1646 26.4903 0.0783 0.0279 0.1089 0.1083 0.0115 2.0749 0.4607 6.0000 6.2786 6.0004 0.3035 0.0777 0.1627 25.7154 0.0749 0.0259 0.1004 0.1082 0.0083 2.1472 0.4455 6.0000 6.2860 6.0004 0.2976 0.0699 0.1608 24.9818 0.0716 0.0239 0.0920 0.1080 0.0050 2.2196 0.4301 6.0000 6.2928 6.0003 0.2914 0.0623 0.1589 24.2861 0.0683 0.0220 0.0837 0.1077 0.0016 2.2919 0.4143 6.0000 6.2989 6.0003 0.2848 0.0549 0.1570 23.6252 0.0650 0.0202 0.0755 0.1073 -0.0018 2.3642 0.3982 6.0000 6.3044 6.0003 0.2778 0.0475 0.1551 22.9963 0.0618 0.0184 0.0674 0.1067 -0.0054 2.4366 0.3818 6.0000 6.3090 6.0003 0.2705 0.0403 0.1533 22.3968 0.0585 0.0167 0.0594 0.1059 -0.0089 2.5089 0.3651 6.0000 6.3127 6.0003 0.2628 0.0332 0.1514 21.8240 0.0553 0.0151 0.0514 0.1050 -0.0125 2.5812 0.3480 6.0000 6.3153 6.0002 0.2547 0.0263 0.1495 21.2759 0.0520 0.0136 0.0436 0.1038 -0.0162 2.6535 0.3307 6.0000 6.3167 6.0002 0.2462 0.0194 0.1476 20.7500 0.0488 0.0121 0.0359 0.1025 -0.0198 2.7259 0.3131 6.0000 6.3165 6.0002 0.2373 0.0127 0.1457 20.2442 0.0456 0.0107 0.0282 0.1009 -0.0235 2.7982 0.2951 5.9916 6.3062 5.9918 0.2280 0.0061 0.1438 19.7322 0.0424 0.0094 0.0206 0.0990 -0.0272 2.8705 0.2768 5.9477 6.2582 5.9478 0.2183 -0.0005 0.1420 19.1359 0.0393 0.0082 0.0132 0.0968 -0.0307 2.9428 0.2583 5.8661 6.1698 5.8662 0.2081 -0.0070 0.1401 18.4525 0.0362 0.0071 0.0058 0.0944 -0.0341 3.0152 0.2394 5.7469 6.0405 5.7469 0.1976 -0.0135 0.1382 17.6846 0.0331 0.0060 -0.0015 0.0916 -0.0374 3.0846 0.2210 5.5970 5.8772 5.5970 0.1870 -0.0196 0.1364 16.8696 0.0301 0.0051 -0.0084 0.0887 -0.0406 3.1039 0.2158 5.5491 5.8247 5.5491 0.1840 -0.0213 0.1359 16.6291 0.0293 0.0048 -0.0103 0.0878 -0.0415 3.1203 0.2113 5.5063 5.7778 5.5064 0.1813 -0.0227 0.1354 16.4203 0.0286 0.0046 -0.0120 0.0870 -0.0422 3.1367 0.2049 5.4615 5.7289 5.4620 0.1769 -0.0247 0.1350 16.2081 0.0277 0.0043 -0.0142 0.0852 -0.0433 3.1532 0.1963 5.4149 5.6781 5.4159 0.1702 -0.0273 0.1346 15.9924 0.0264 0.0040 -0.0172 0.0823 -0.0448 3.1696 0.1849 5.3663 5.6252 5.3758 0.1609 -0.0305 0.1342 15.7728 0.0248 0.0035 -0.0210 0.0779 -0.0468 3.1860 0.1701 5.3157 5.5701 5.3469 0.1482 -0.0346 0.1337 15.5493 0.0227 0.0030 -0.0259 0.0717 -0.0495 3.2024 0.1504 5.2632 5.5126 5.3332 0.1309 -0.0400 0.1333 15.3214 0.0200 0.0023 -0.0322 0.0629 -0.0529 3.2188 0.1218 5.2088 5.4529 5.3628 0.1048 -0.0475 0.1329 15.0893 0.0162 0.0015 -0.0411 0.0494 -0.0579 3.2352 0.0672 5.1524 5.3922 5.6867 0.0536 -0.0614 0.1325 14.8563 0.0089 0.0005 -0.0579 0.0222 -0.0673 3.2500 0.0088 5.1000 5.1000 5.1000 -0.0015 -0.0761 0.1321 14.0229 0.0012 0.0000 -0.0761 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) = 0.022800 TOTAL WEIGHT (Kg) = 0.010340 TOTAL VOLUME (IN**3) = 0.371443 TOTAL PROJECTED AREA (IN**2) = 2.6745 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000075 MOMENT OF INERTIA (Kg-M**2) = 0.000008 STATIC MOMENT, ONE SIDE (IN-LB) = 0.009995 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) = 49349.88 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.