6x2 (6x2.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 2.0000 0.0000 0.0000 0.3250 0.0000 0.2292 0.0000 0.1490 0.0000 0.1050 0.0000 0.0000 0.0750 0.6249 2.0000 0.0051 -0.2068 0.3225 0.0037 0.2262 0.6259 0.1413 0.1312 0.1065 0.0092 -0.0169 0.1500 0.5962 2.0000 0.0399 -0.3989 0.3222 0.0134 0.2232 2.4239 0.1331 0.1253 0.1105 0.0235 -0.0140 0.2250 0.5671 2.0000 0.1301 -0.5275 0.3236 0.0274 0.2202 5.2570 0.1249 0.1154 0.1156 0.0413 -0.0095 0.3000 0.5405 2.0000 0.2965 -0.5431 0.3264 0.0439 0.2173 8.9378 0.1174 0.1027 0.1213 0.0609 -0.0037 0.3750 0.5192 2.0000 0.5510 -0.4094 0.3302 0.0611 0.2143 13.1628 0.1113 0.0889 0.1274 0.0809 0.0030 0.4500 0.5050 2.0000 0.8905 -0.1115 0.3345 0.0775 0.2114 17.4812 0.1068 0.0758 0.1334 0.0997 0.0101 0.5250 0.4985 2.0000 1.2881 0.3292 0.3389 0.0914 0.2085 21.3295 0.1040 0.0643 0.1388 0.1159 0.0171 0.6000 0.4995 2.0000 1.6881 0.8426 0.3431 0.1011 0.2057 24.1215 0.1027 0.0553 0.1425 0.1279 0.0233 0.6750 0.5070 2.0000 2.0088 1.3081 0.3466 0.1049 0.2028 25.3449 0.1028 0.0494 0.1433 0.1339 0.0275 0.7500 0.5208 2.0000 2.1597 1.5758 0.3490 0.1011 0.2000 24.6225 0.1042 0.0474 0.1400 0.1315 0.0282 0.8247 0.5370 2.0000 2.1747 1.6585 0.3504 0.0924 0.1972 22.7665 0.1059 0.0477 0.1339 0.1234 0.0260 0.8948 0.5485 2.0000 2.1873 1.7264 0.3510 0.0847 0.1946 21.2577 0.1068 0.0476 0.1283 0.1173 0.0241 0.9647 0.5562 2.0000 2.1995 1.7865 0.3511 0.0776 0.1921 19.9450 0.1068 0.0470 0.1228 0.1126 0.0223 1.0345 0.5602 2.0000 2.2113 1.8389 0.3506 0.0711 0.1895 18.7886 0.1062 0.0461 0.1174 0.1092 0.0207 1.1043 0.5606 2.0000 2.2227 1.8839 0.3496 0.0651 0.1870 17.7622 0.1048 0.0447 0.1121 0.1070 0.0193 1.1741 0.5573 2.0000 2.2337 1.9215 0.3480 0.0596 0.1845 16.8449 0.1028 0.0430 0.1069 0.1061 0.0181 1.2440 0.5502 2.0000 2.2441 1.9516 0.3459 0.0547 0.1820 16.0197 0.1001 0.0409 0.1017 0.1065 0.0171 1.3138 0.5396 2.0000 2.2541 1.9745 0.3433 0.0502 0.1795 15.2731 0.0969 0.0385 0.0966 0.1080 0.0163 1.3836 0.5276 2.0000 2.2636 1.9901 0.3401 0.0461 0.1771 14.5946 0.0934 0.0361 0.0917 0.1097 0.0154 1.4534 0.5153 2.0000 2.2728 1.9984 0.3365 0.0422 0.1746 13.9753 0.0900 0.0339 0.0868 0.1111 0.0143 1.5233 0.5026 2.0000 2.2815 2.0000 0.3323 0.0385 0.1721 13.4076 0.0865 0.0318 0.0819 0.1122 0.0130 1.5931 0.4897 2.0000 2.2898 2.0000 0.3277 0.0349 0.1697 12.8850 0.0831 0.0297 0.0772 0.1131 0.0116 1.6629 0.4764 2.0000 2.2976 2.0000 0.3225 0.0315 0.1672 12.4021 0.0797 0.0277 0.0726 0.1136 0.0102 1.7328 0.4628 2.0000 2.3051 2.0000 0.3169 0.0283 0.1648 11.9542 0.0763 0.0258 0.0680 0.1138 0.0088 1.8026 0.4490 2.0000 2.3120 2.0000 0.3109 0.0253 0.1623 11.5375 0.0729 0.0239 0.0635 0.1137 0.0074 1.8724 0.4348 2.0000 2.3185 2.0000 0.3044 0.0223 0.1598 11.1486 0.0695 0.0221 0.0591 0.1133 0.0059 1.9422 0.4203 2.0000 2.3245 2.0000 0.2975 0.0195 0.1574 10.7844 0.0661 0.0203 0.0548 0.1127 0.0045 2.0121 0.4054 2.0000 2.3300 2.0000 0.2901 0.0168 0.1549 10.4425 0.0628 0.0186 0.0506 0.1117 0.0031 2.0819 0.3903 2.0000 2.3349 2.0000 0.2823 0.0142 0.1524 10.1207 0.0595 0.0170 0.0465 0.1105 0.0016 2.1517 0.3749 2.0000 2.3394 2.0000 0.2741 0.0118 0.1500 9.8169 0.0562 0.0154 0.0424 0.1090 0.0002 2.2216 0.3591 2.0000 2.3432 2.0000 0.2655 0.0094 0.1475 9.5294 0.0530 0.0139 0.0385 0.1072 -0.0011 2.2914 0.3431 1.9991 2.3455 1.9991 0.2565 0.0072 0.1450 9.2531 0.0498 0.0125 0.0346 0.1052 -0.0025 2.3612 0.3267 1.9934 2.3425 1.9934 0.2471 0.0050 0.1426 8.9725 0.0466 0.0112 0.0308 0.1029 -0.0038 2.4310 0.3100 1.9825 2.3335 1.9825 0.2374 0.0029 0.1401 8.6860 0.0434 0.0099 0.0271 0.1004 -0.0050 2.5009 0.2931 1.9664 2.3187 1.9664 0.2273 0.0008 0.1376 8.3940 0.0403 0.0087 0.0235 0.0977 -0.0062 2.5707 0.2758 1.9452 2.2978 1.9451 0.2168 -0.0011 0.1352 8.0966 0.0373 0.0076 0.0199 0.0948 -0.0074 2.6405 0.2582 1.9187 2.2708 1.9187 0.2060 -0.0030 0.1327 7.7938 0.0343 0.0065 0.0164 0.0916 -0.0085 2.7103 0.2403 1.8870 2.2377 1.8870 0.1948 -0.0049 0.1303 7.4857 0.0313 0.0055 0.0131 0.0883 -0.0096 2.7802 0.2221 1.8501 2.1981 1.8501 0.1833 -0.0066 0.1278 7.1721 0.0284 0.0047 0.0098 0.0848 -0.0107 2.8471 0.2043 1.8098 2.1540 1.8098 0.1720 -0.0082 0.1254 6.8658 0.0256 0.0039 0.0067 0.0812 -0.0116 2.8652 0.1995 1.7982 2.1411 1.7982 0.1689 -0.0086 0.1248 6.7825 0.0249 0.0037 0.0059 0.0802 -0.0119 2.8803 0.1950 1.7881 2.1299 1.7882 0.1660 -0.0090 0.1243 6.7123 0.0242 0.0035 0.0051 0.0792 -0.0122 2.8955 0.1888 1.7778 2.1189 1.7785 0.1612 -0.0096 0.1237 6.6432 0.0234 0.0033 0.0041 0.0772 -0.0126 2.9106 0.1806 1.7673 2.1078 1.7710 0.1545 -0.0104 0.1232 6.5748 0.0222 0.0030 0.0026 0.0740 -0.0132 2.9258 0.1699 1.7565 2.0967 1.7662 0.1453 -0.0115 0.1227 6.5068 0.0208 0.0026 0.0008 0.0695 -0.0141 2.9409 0.1560 1.7454 2.0854 1.7646 0.1329 -0.0129 0.1221 6.4389 0.0191 0.0022 -0.0017 0.0633 -0.0152 2.9561 0.1377 1.7341 2.0738 1.7694 0.1161 -0.0147 0.1216 6.3710 0.0167 0.0017 -0.0049 0.0546 -0.0168 2.9712 0.1110 1.7226 2.0621 1.7925 0.0910 -0.0175 0.1210 6.3032 0.0134 0.0011 -0.0096 0.0412 -0.0191 2.9864 0.0606 1.7108 2.0520 1.9334 0.0424 -0.0227 0.1205 6.2411 0.0073 0.0003 -0.0184 0.0148 -0.0237 3.0000 0.0081 1.7000 1.7000 1.7000 -0.0085 -0.0283 0.1200 5.1535 0.0010 0.0000 -0.0283 0.0000 0.0000 RADIUS: 3.00 PROPELLER RADIUS (IN) HUBRAD: 0.32 HUB RADIUS (IN) HUBTRA: 0.75 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.014847 TOTAL WEIGHT (Kg) = 0.006734 TOTAL VOLUME (IN**3) = 0.241884 TOTAL PROJECTED AREA (IN**2) = 2.5697 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000044 MOMENT OF INERTIA (Kg-M**2) = 0.000005 STATIC MOMENT, ONE SIDE (IN-LB) = 0.006093 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 = 80.319 INNER LIMIT (NORMALIZED BY RADIUS) = 0.108 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 42652.37 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.