6.5x5.5 (65x55.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 2.9842 0.0000 0.0000 0.3250 0.0000 0.4462 0.0000 0.2900 0.0000 0.1050 0.0000 0.0000 0.0900 0.6198 3.2553 0.0099 -0.3240 0.3223 0.0062 0.4444 1.0057 0.2754 0.1525 0.1100 0.0110 -0.0336 0.1800 0.5857 3.5110 0.0782 -0.6340 0.3228 0.0228 0.4392 3.9545 0.2573 0.1493 0.1236 0.0292 -0.0270 0.2700 0.5530 3.7512 0.2610 -0.8489 0.3257 0.0469 0.4306 8.7464 0.2381 0.1441 0.1434 0.0503 -0.0159 0.3600 0.5270 3.9760 0.6101 -0.8775 0.3304 0.0759 0.4185 15.0956 0.2205 0.1366 0.1670 0.0729 -0.0017 0.4500 0.5123 4.1853 1.1646 -0.6407 0.3360 0.1070 0.4029 22.3860 0.2064 0.1278 0.1918 0.0951 0.0137 0.5400 0.5108 4.3791 1.9336 -0.0872 0.3421 0.1376 0.3839 29.6791 0.1961 0.1184 0.2153 0.1153 0.0287 0.6300 0.5210 4.5575 2.8719 0.7730 0.3477 0.1652 0.3614 35.9618 0.1883 0.1093 0.2351 0.1316 0.0416 0.7200 0.5386 4.7205 3.8561 1.8307 0.3523 0.1870 0.3354 40.4440 0.1807 0.1011 0.2487 0.1423 0.0510 0.8100 0.5587 4.8679 4.6871 2.8619 0.3552 0.2003 0.3060 42.6436 0.1710 0.0939 0.2541 0.1455 0.0557 0.9000 0.5776 5.0000 5.1387 3.5714 0.3557 0.2027 0.2740 42.2622 0.1582 0.0874 0.2495 0.1402 0.0547 0.9891 0.5927 5.1155 5.2714 3.9470 0.3543 0.1972 0.2458 40.3059 0.1457 0.0804 0.2383 0.1304 0.0508 1.0623 0.6007 5.1991 5.3623 4.2291 0.3528 0.1921 0.2264 38.7772 0.1360 0.0742 0.2292 0.1233 0.0484 1.1347 0.6047 5.2716 5.4396 4.4839 0.3512 0.1865 0.2105 37.3437 0.1273 0.0682 0.2203 0.1174 0.0467 1.2070 0.6049 5.3341 5.5062 4.7134 0.3492 0.1803 0.1979 35.9817 0.1197 0.0624 0.2116 0.1125 0.0454 1.2793 0.6013 5.3867 5.5634 4.9157 0.3470 0.1735 0.1886 34.6882 0.1134 0.0572 0.2029 0.1088 0.0444 1.3516 0.5940 5.4292 5.6127 5.0893 0.3446 0.1660 0.1825 33.4603 0.1084 0.0525 0.1943 0.1064 0.0437 1.4240 0.5830 5.4618 5.6549 5.2329 0.3418 0.1579 0.1796 32.2946 0.1047 0.0486 0.1858 0.1053 0.0431 1.4963 0.5707 5.4844 5.6880 5.3453 0.3388 0.1497 0.1777 31.1746 0.1014 0.0451 0.1774 0.1049 0.0422 1.5686 0.5581 5.4971 5.7109 5.4259 0.3355 0.1416 0.1759 30.0897 0.0981 0.0420 0.1690 0.1047 0.0411 1.6409 0.5452 5.5000 5.7238 5.4743 0.3319 0.1336 0.1740 29.0367 0.0948 0.0392 0.1608 0.1047 0.0397 1.7133 0.5319 5.5000 5.7334 5.4971 0.3279 0.1258 0.1721 28.0401 0.0915 0.0367 0.1527 0.1048 0.0379 1.7856 0.5183 5.5000 5.7428 5.5000 0.3237 0.1181 0.1702 27.1065 0.0882 0.0344 0.1446 0.1051 0.0358 1.8579 0.5044 5.5000 5.7519 5.5001 0.3192 0.1106 0.1683 26.2303 0.0849 0.0322 0.1366 0.1054 0.0334 1.9303 0.4902 5.5000 5.7605 5.5003 0.3143 0.1033 0.1664 25.4064 0.0816 0.0300 0.1287 0.1057 0.0310 2.0026 0.4756 5.5000 5.7689 5.5003 0.3091 0.0961 0.1646 24.6304 0.0783 0.0279 0.1209 0.1059 0.0284 2.0749 0.4608 5.5000 5.7767 5.5003 0.3035 0.0890 0.1627 23.8982 0.0750 0.0259 0.1132 0.1061 0.0257 2.1472 0.4456 5.5000 5.7841 5.5003 0.2976 0.0821 0.1608 23.2060 0.0716 0.0239 0.1056 0.1061 0.0229 2.2196 0.4301 5.5000 5.7910 5.5003 0.2914 0.0753 0.1589 22.5504 0.0683 0.0220 0.0980 0.1059 0.0200 2.2919 0.4143 5.5000 5.7972 5.5003 0.2848 0.0686 0.1570 21.9284 0.0651 0.0202 0.0906 0.1057 0.0171 2.3642 0.3982 5.5000 5.8028 5.5003 0.2778 0.0621 0.1551 21.3371 0.0618 0.0184 0.0832 0.1052 0.0141 2.4366 0.3818 5.5000 5.8075 5.5003 0.2705 0.0557 0.1533 20.7740 0.0585 0.0167 0.0759 0.1046 0.0110 2.5089 0.3651 5.5000 5.8113 5.5002 0.2628 0.0494 0.1514 20.2364 0.0553 0.0151 0.0687 0.1038 0.0079 2.5812 0.3481 5.5000 5.8140 5.5002 0.2547 0.0432 0.1495 19.7221 0.0520 0.0136 0.0616 0.1027 0.0048 2.6535 0.3307 5.5000 5.8155 5.5002 0.2462 0.0371 0.1476 19.2290 0.0488 0.0121 0.0546 0.1015 0.0016 2.7259 0.3131 5.5000 5.8155 5.5002 0.2373 0.0312 0.1457 18.7549 0.0456 0.0107 0.0476 0.0999 -0.0016 2.7982 0.2951 5.5000 5.8137 5.5001 0.2280 0.0253 0.1438 18.2976 0.0424 0.0094 0.0407 0.0982 -0.0048 2.8705 0.2769 5.5000 5.8098 5.5001 0.2183 0.0195 0.1420 17.8550 0.0393 0.0082 0.0339 0.0962 -0.0080 2.9428 0.2583 5.5000 5.8033 5.5001 0.2081 0.0139 0.1401 17.4247 0.0362 0.0071 0.0272 0.0939 -0.0112 3.0152 0.2394 5.4961 5.7896 5.4962 0.1976 0.0083 0.1382 16.9933 0.0331 0.0060 0.0206 0.0913 -0.0144 3.0846 0.2210 5.4681 5.7483 5.4682 0.1870 0.0030 0.1364 16.5200 0.0301 0.0051 0.0144 0.0885 -0.0174 3.1039 0.2158 5.4555 5.7311 5.4555 0.1840 0.0016 0.1359 16.3764 0.0293 0.0048 0.0126 0.0877 -0.0182 3.1203 0.2113 5.4431 5.7146 5.4432 0.1813 0.0003 0.1354 16.2504 0.0286 0.0046 0.0111 0.0869 -0.0189 3.1367 0.2050 5.4292 5.6966 5.4296 0.1769 -0.0014 0.1350 16.1215 0.0277 0.0043 0.0090 0.0852 -0.0199 3.1532 0.1964 5.4139 5.6771 5.4149 0.1703 -0.0038 0.1346 15.9896 0.0264 0.0040 0.0062 0.0823 -0.0214 3.1696 0.1850 5.3969 5.6558 5.4062 0.1610 -0.0069 0.1342 15.8544 0.0248 0.0035 0.0026 0.0780 -0.0234 3.1860 0.1702 5.3785 5.6328 5.4093 0.1484 -0.0109 0.1337 15.7158 0.0228 0.0030 -0.0022 0.0718 -0.0259 3.2024 0.1506 5.3586 5.6079 5.4280 0.1311 -0.0161 0.1333 15.5734 0.0201 0.0023 -0.0084 0.0630 -0.0294 3.2188 0.1220 5.3372 5.5811 5.4905 0.1051 -0.0236 0.1329 15.4273 0.0162 0.0015 -0.0174 0.0496 -0.0344 3.2352 0.0674 5.3142 5.5536 5.8480 0.0540 -0.0379 0.1325 15.2807 0.0089 0.0005 -0.0344 0.0226 -0.0440 3.2500 0.0088 5.2923 5.2923 5.2922 -0.0011 -0.0530 0.1321 14.5295 0.0012 0.0000 -0.0530 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) = 0.022789 TOTAL WEIGHT (Kg) = 0.010335 TOTAL VOLUME (IN**3) = 0.371255 TOTAL PROJECTED AREA (IN**2) = 2.6949 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000075 MOMENT OF INERTIA (Kg-M**2) = 0.000008 STATIC MOMENT, ONE SIDE (IN-LB) = 0.009987 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) = 49324.98 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.