6x3 (6x3.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 -0.7552 0.0000 0.0000 0.3250 0.0000 0.2492 0.0000 0.1620 0.0000 0.1050 0.0000 0.0000 0.0750 0.6250 -0.3344 0.0047 -0.2072 0.3225 0.0028 0.2462 0.5686 0.1539 0.1311 0.1059 0.0091 -0.0174 0.1500 0.5967 0.0614 0.0366 -0.4004 0.3222 0.0102 0.2432 2.2211 0.1451 0.1251 0.1082 0.0233 -0.0160 0.2250 0.5677 0.4322 0.1209 -0.5319 0.3236 0.0210 0.2402 4.8865 0.1364 0.1155 0.1111 0.0408 -0.0136 0.3000 0.5409 0.7780 0.2795 -0.5522 0.3264 0.0339 0.2373 8.4356 0.1283 0.1033 0.1145 0.0602 -0.0105 0.3750 0.5191 1.0988 0.5281 -0.4233 0.3302 0.0477 0.2343 12.6340 0.1216 0.0904 0.1181 0.0800 -0.0070 0.4500 0.5041 1.3946 0.8703 -0.1254 0.3345 0.0613 0.2314 17.1093 0.1167 0.0782 0.1220 0.0988 -0.0032 0.5250 0.4972 1.6654 1.2905 0.3298 0.3389 0.0733 0.2285 21.3664 0.1136 0.0675 0.1257 0.1151 0.0006 0.6000 0.4980 1.9112 1.7469 0.8856 0.3431 0.0827 0.2257 24.8619 0.1124 0.0593 0.1288 0.1274 0.0038 0.6750 0.5060 2.1320 2.1705 1.4350 0.3466 0.0882 0.2228 27.1026 0.1128 0.0541 0.1305 0.1340 0.0057 0.7500 0.5203 2.3278 2.4756 1.8336 0.3490 0.0887 0.2200 27.7146 0.1145 0.0527 0.1301 0.1328 0.0050 0.8247 0.5365 2.4981 2.6621 2.0696 0.3504 0.0856 0.2172 27.1907 0.1165 0.0536 0.1281 0.1264 0.0029 0.8948 0.5479 2.6352 2.8130 2.2724 0.3510 0.0828 0.2146 26.5798 0.1176 0.0537 0.1260 0.1212 0.0018 0.9647 0.5556 2.7501 2.9410 2.4540 0.3511 0.0800 0.2121 25.8837 0.1178 0.0531 0.1238 0.1168 0.0016 1.0345 0.5596 2.8434 3.0466 2.6120 0.3506 0.0772 0.2095 25.1135 0.1173 0.0521 0.1215 0.1133 0.0021 1.1043 0.5600 2.9149 3.1299 2.7437 0.3496 0.0745 0.2070 24.2793 0.1159 0.0505 0.1190 0.1108 0.0032 1.1741 0.5567 2.9648 3.1907 2.8469 0.3480 0.0718 0.2045 23.3887 0.1139 0.0485 0.1164 0.1094 0.0049 1.2440 0.5498 2.9930 3.2291 2.9196 0.3459 0.0692 0.2020 22.4474 0.1111 0.0461 0.1137 0.1091 0.0071 1.3138 0.5392 3.0000 3.2454 2.9612 0.3433 0.0667 0.1995 21.4626 0.1076 0.0434 0.1108 0.1099 0.0097 1.3836 0.5273 3.0000 3.2542 2.9849 0.3401 0.0642 0.1971 20.5221 0.1039 0.0407 0.1078 0.1110 0.0119 1.4534 0.5150 3.0000 3.2626 2.9976 0.3365 0.0618 0.1946 19.6595 0.1002 0.0382 0.1046 0.1119 0.0137 1.5233 0.5024 3.0000 3.2704 3.0000 0.3323 0.0593 0.1921 18.8654 0.0965 0.0359 0.1013 0.1126 0.0149 1.5931 0.4895 3.0000 3.2779 3.0001 0.3277 0.0568 0.1897 18.1319 0.0928 0.0337 0.0979 0.1131 0.0158 1.6629 0.4762 3.0000 3.2848 3.0001 0.3225 0.0543 0.1872 17.4519 0.0892 0.0315 0.0944 0.1133 0.0164 1.7328 0.4627 3.0000 3.2911 3.0001 0.3169 0.0517 0.1848 16.8197 0.0855 0.0293 0.0907 0.1133 0.0167 1.8026 0.4488 3.0000 3.2969 3.0002 0.3109 0.0490 0.1823 16.2300 0.0818 0.0272 0.0868 0.1130 0.0167 1.8724 0.4346 3.0000 3.3021 3.0001 0.3044 0.0463 0.1798 15.6784 0.0782 0.0252 0.0829 0.1124 0.0165 1.9422 0.4201 3.0000 3.3067 3.0001 0.2975 0.0436 0.1774 15.1610 0.0745 0.0233 0.0788 0.1116 0.0159 2.0121 0.4053 3.0000 3.3106 3.0001 0.2901 0.0407 0.1749 14.6743 0.0709 0.0214 0.0745 0.1104 0.0152 2.0819 0.3902 3.0000 3.3137 3.0001 0.2823 0.0378 0.1724 14.2152 0.0673 0.0195 0.0702 0.1091 0.0142 2.1517 0.3748 3.0000 3.3160 3.0001 0.2741 0.0347 0.1700 13.7811 0.0637 0.0178 0.0657 0.1075 0.0130 2.2216 0.3591 3.0000 3.3175 3.0001 0.2655 0.0316 0.1675 13.3694 0.0601 0.0161 0.0610 0.1056 0.0116 2.2914 0.3430 2.9986 3.3166 2.9988 0.2565 0.0283 0.1650 12.9727 0.0566 0.0145 0.0563 0.1035 0.0099 2.3612 0.3267 2.9901 3.3076 2.9902 0.2471 0.0249 0.1626 12.5681 0.0531 0.0130 0.0513 0.1012 0.0081 2.4310 0.3100 2.9738 3.2895 2.9739 0.2374 0.0214 0.1601 12.1535 0.0496 0.0115 0.0463 0.0986 0.0061 2.5009 0.2930 2.9497 3.2624 2.9498 0.2273 0.0177 0.1576 11.7289 0.0462 0.0102 0.0411 0.0958 0.0039 2.5707 0.2757 2.9177 3.2259 2.9178 0.2168 0.0139 0.1552 11.2944 0.0428 0.0089 0.0358 0.0928 0.0016 2.6405 0.2581 2.8780 3.1798 2.8781 0.2060 0.0100 0.1527 10.8497 0.0394 0.0077 0.0303 0.0897 -0.0010 2.7103 0.2402 2.8305 3.1238 2.8305 0.1948 0.0059 0.1503 10.3944 0.0361 0.0066 0.0247 0.0863 -0.0037 2.7802 0.2220 2.7751 3.0573 2.7752 0.1833 0.0017 0.1478 9.9275 0.0328 0.0055 0.0190 0.0827 -0.0067 2.8471 0.2043 2.7147 2.9832 2.7148 0.1720 -0.0025 0.1454 9.4676 0.0297 0.0046 0.0134 0.0791 -0.0097 2.8652 0.1994 2.6973 2.9615 2.6973 0.1689 -0.0036 0.1448 9.3417 0.0289 0.0044 0.0118 0.0781 -0.0105 2.8803 0.1951 2.6822 2.9426 2.6823 0.1660 -0.0046 0.1443 9.2352 0.0281 0.0042 0.0105 0.0771 -0.0113 2.8955 0.1889 2.6667 2.9234 2.6672 0.1614 -0.0059 0.1437 9.1289 0.0272 0.0039 0.0087 0.0752 -0.0123 2.9106 0.1807 2.6509 2.9039 2.6551 0.1547 -0.0075 0.1432 9.0226 0.0259 0.0036 0.0064 0.0721 -0.0135 2.9258 0.1700 2.6347 2.8839 2.6516 0.1455 -0.0095 0.1427 8.9159 0.0243 0.0032 0.0036 0.0677 -0.0151 2.9409 0.1562 2.6181 2.8635 2.6563 0.1333 -0.0120 0.1421 8.8087 0.0222 0.0027 0.0001 0.0616 -0.0170 2.9561 0.1379 2.6012 2.8424 2.6774 0.1166 -0.0151 0.1416 8.7006 0.0195 0.0021 -0.0044 0.0531 -0.0195 2.9712 0.1112 2.5839 2.8207 2.7431 0.0916 -0.0193 0.1410 8.5918 0.0157 0.0014 -0.0108 0.0400 -0.0229 2.9864 0.0608 2.5662 2.7996 3.1004 0.0432 -0.0270 0.1405 8.4861 0.0085 0.0004 -0.0224 0.0142 -0.0291 3.0000 0.0081 2.5500 2.5500 2.5500 -0.0077 -0.0350 0.1400 7.7043 0.0011 0.0000 -0.0350 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) = 0.015918 TOTAL WEIGHT (Kg) = 0.007219 TOTAL VOLUME (IN**3) = 0.259327 TOTAL PROJECTED AREA (IN**2) = 2.5213 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000050 MOMENT OF INERTIA (Kg-M**2) = 0.000006 STATIC MOMENT, ONE SIDE (IN-LB) = 0.006824 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) = 45394.40 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.