9x3N (9x3N.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 0.8000 3.0000 -0.5000 -0.5000 0.4000 0.0000 0.3312 0.0000 0.2650 0.0000 0.0500 0.0000 0.0000 0.1375 0.7624 3.0000 -0.4885 -0.9743 0.3944 0.0020 0.3168 -29.4865 0.2415 0.1748 0.0524 0.0092 -0.0767 0.2750 0.7322 3.0000 -0.4123 -1.4046 0.3913 0.0073 0.3029 -13.4200 0.2218 0.1726 0.0586 0.0222 -0.0768 0.4125 0.7100 3.0000 -0.2215 -1.6698 0.3900 0.0149 0.2895 -4.8856 0.2055 0.1671 0.0670 0.0354 -0.0763 0.5500 0.6961 3.0000 0.1122 -1.6780 0.3902 0.0238 0.2766 1.8590 0.1925 0.1586 0.0770 0.0486 -0.0747 0.6875 0.6899 3.0000 0.5916 -1.3867 0.3915 0.0331 0.2642 7.7981 0.1823 0.1479 0.0876 0.0616 -0.0717 0.8250 0.6894 3.0000 1.1912 -0.8073 0.3935 0.0419 0.2523 12.9422 0.1740 0.1357 0.0979 0.0744 -0.0670 0.9625 0.6914 3.0000 1.8568 -0.0080 0.3958 0.0493 0.2410 17.0683 0.1666 0.1227 0.1066 0.0866 -0.0606 1.1000 0.6916 3.0000 2.5054 0.8861 0.3979 0.0544 0.2301 19.9257 0.1591 0.1092 0.1122 0.0981 -0.0527 1.2375 0.6859 3.0000 3.0256 1.6933 0.3994 0.0562 0.2198 21.2620 0.1508 0.0959 0.1137 0.1082 -0.0440 1.3750 0.6709 3.0000 3.2751 2.1727 0.4000 0.0538 0.2100 20.7612 0.1409 0.0834 0.1096 0.1159 -0.0355 1.5103 0.6500 3.0000 3.2891 2.3265 0.3995 0.0487 0.2008 19.1164 0.1305 0.0725 0.1019 0.1215 -0.0285 1.6078 0.6355 3.0000 3.2963 2.4317 0.3988 0.0453 0.1945 18.0718 0.1236 0.0656 0.0965 0.1253 -0.0245 1.7030 0.6216 3.0000 3.3024 2.5302 0.3978 0.0420 0.1886 17.1517 0.1172 0.0596 0.0914 0.1289 -0.0214 1.7983 0.6081 3.0000 3.3078 2.6232 0.3964 0.0390 0.1830 16.3175 0.1113 0.0543 0.0864 0.1322 -0.0189 1.8935 0.5949 3.0000 3.3124 2.7091 0.3948 0.0360 0.1776 15.5578 0.1056 0.0495 0.0815 0.1352 -0.0170 1.9888 0.5820 3.0000 3.3163 2.7866 0.3927 0.0331 0.1724 14.8630 0.1003 0.0453 0.0768 0.1379 -0.0155 2.0841 0.5693 3.0000 3.3196 2.8543 0.3903 0.0303 0.1675 14.2254 0.0954 0.0415 0.0722 0.1403 -0.0145 2.1793 0.5569 3.0000 3.3224 2.9108 0.3875 0.0275 0.1628 13.6382 0.0907 0.0382 0.0677 0.1423 -0.0139 2.2746 0.5444 3.0000 3.3246 2.9546 0.3843 0.0248 0.1584 13.0958 0.0862 0.0352 0.0633 0.1440 -0.0136 2.3698 0.5319 3.0000 3.3265 2.9845 0.3806 0.0223 0.1542 12.5933 0.0820 0.0326 0.0591 0.1454 -0.0135 2.4651 0.5194 3.0000 3.3280 2.9989 0.3766 0.0197 0.1503 12.1266 0.0780 0.0302 0.0551 0.1465 -0.0137 2.5603 0.5067 3.0000 3.3292 3.0000 0.3721 0.0173 0.1466 11.6921 0.0743 0.0281 0.0511 0.1472 -0.0140 2.6556 0.4940 3.0000 3.3301 3.0000 0.3671 0.0149 0.1431 11.2868 0.0707 0.0261 0.0473 0.1476 -0.0145 2.7509 0.4810 3.0000 3.3309 3.0001 0.3616 0.0126 0.1399 10.9079 0.0673 0.0242 0.0437 0.1476 -0.0149 2.8461 0.4679 3.0000 3.3315 3.0001 0.3556 0.0104 0.1370 10.5531 0.0641 0.0224 0.0401 0.1471 -0.0155 2.9414 0.4546 3.0000 3.3321 3.0001 0.3491 0.0082 0.1343 10.2203 0.0611 0.0208 0.0367 0.1463 -0.0160 3.0366 0.4411 3.0000 3.3326 3.0001 0.3421 0.0061 0.1318 9.9077 0.0582 0.0192 0.0334 0.1451 -0.0165 3.1319 0.4274 3.0000 3.3331 3.0001 0.3346 0.0041 0.1296 9.6135 0.0554 0.0178 0.0303 0.1434 -0.0171 3.2272 0.4133 3.0000 3.3336 3.0001 0.3265 0.0022 0.1277 9.3363 0.0528 0.0164 0.0273 0.1413 -0.0176 3.3224 0.3990 3.0000 3.3342 3.0001 0.3178 0.0003 0.1259 9.0746 0.0502 0.0151 0.0244 0.1388 -0.0181 3.4177 0.3844 3.0000 3.3348 3.0001 0.3085 -0.0014 0.1245 8.8273 0.0478 0.0138 0.0217 0.1359 -0.0186 3.5129 0.3694 3.0000 3.3355 3.0001 0.2986 -0.0031 0.1232 8.5932 0.0455 0.0127 0.0191 0.1325 -0.0190 3.6082 0.3542 3.0000 3.3361 3.0001 0.2881 -0.0047 0.1223 8.3712 0.0433 0.0116 0.0166 0.1286 -0.0193 3.7034 0.3385 3.0000 3.3366 3.0001 0.2770 -0.0061 0.1215 8.1601 0.0411 0.0105 0.0143 0.1243 -0.0196 3.7987 0.3225 3.0000 3.3389 2.9970 0.2652 -0.0074 0.1210 7.9634 0.0390 0.0095 0.0121 0.1195 -0.0199 3.8940 0.3060 3.0000 3.3578 2.9756 0.2527 -0.0084 0.1208 7.8144 0.0370 0.0086 0.0100 0.1143 -0.0201 3.9892 0.2891 3.0000 3.4058 2.9418 0.2396 -0.0090 0.1208 7.7378 0.0349 0.0077 0.0081 0.1086 -0.0202 4.0845 0.2717 3.0000 3.4948 2.9056 0.2257 -0.0090 0.1210 7.7547 0.0329 0.0068 0.0065 0.1025 -0.0202 4.1797 0.2539 3.0000 3.6379 2.8774 0.2112 -0.0086 0.1215 7.8865 0.0309 0.0060 0.0052 0.0959 -0.0199 4.2712 0.2364 2.9746 3.8134 2.8432 0.1965 -0.0077 0.1222 8.0874 0.0289 0.0052 0.0044 0.0890 -0.0193 4.2977 0.2312 2.9522 3.8627 2.8232 0.1922 -0.0074 0.1225 8.1405 0.0283 0.0050 0.0042 0.0870 -0.0191 4.3205 0.2266 2.9275 3.9046 2.8026 0.1882 -0.0071 0.1227 8.1850 0.0278 0.0048 0.0040 0.0851 -0.0189 4.3432 0.2200 2.8975 3.9466 2.7795 0.1822 -0.0071 0.1229 8.2291 0.0270 0.0045 0.0034 0.0821 -0.0189 4.3659 0.2106 2.8624 3.9892 2.7684 0.1735 -0.0076 0.1232 8.2741 0.0259 0.0042 0.0023 0.0775 -0.0191 4.3886 0.1982 2.8221 4.0321 2.7703 0.1618 -0.0085 0.1235 8.3192 0.0245 0.0037 0.0006 0.0713 -0.0197 4.4114 0.1820 2.7766 4.0757 2.7911 0.1463 -0.0101 0.1238 8.3651 0.0225 0.0031 -0.0018 0.0631 -0.0206 4.4341 0.1611 2.7260 4.1200 2.8483 0.1262 -0.0124 0.1240 8.4119 0.0200 0.0025 -0.0053 0.0523 -0.0220 4.4568 0.1330 2.6702 4.1645 2.9886 0.0990 -0.0159 0.1244 8.4588 0.0165 0.0017 -0.0101 0.0377 -0.0241 4.4795 0.0917 2.6093 4.2092 3.4291 0.0588 -0.0216 0.1247 8.5055 0.0114 0.0008 -0.0177 0.0158 -0.0275 4.5000 0.0088 2.5500 2.5500 2.5500 -0.0225 -0.0350 0.1250 5.1535 0.0011 0.0000 -0.0350 0.0000 0.0000 RADIUS: 4.50 PROPELLER RADIUS (IN) HUBRAD: 0.40 HUB RADIUS (IN) HUBTRA: 1.38 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.034140 TOTAL WEIGHT (Kg) = 0.015483 TOTAL VOLUME (IN**3) = 0.556185 TOTAL PROJECTED AREA (IN**2) = 4.5452 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000187 MOMENT OF INERTIA (Kg-M**2) = 0.000021 STATIC MOMENT, ONE SIDE (IN-LB) = 0.019090 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 = 60.121 INNER LIMIT (NORMALIZED BY RADIUS) = 0.089 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 23891.15 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.50, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 3.75, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.