5.5x2 (55x2.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 0.2643 0.0000 0.1718 0.0000 0.1050 0.0000 0.0000 0.0750 0.6250 2.0000 0.0049 -0.2066 0.3225 0.0036 0.2566 0.5903 0.1604 0.1312 0.1065 0.0091 -0.0169 0.1500 0.5965 2.0000 0.0377 -0.4000 0.3222 0.0132 0.2493 2.2890 0.1487 0.1252 0.1105 0.0233 -0.0138 0.2250 0.5676 2.0000 0.1237 -0.5304 0.3236 0.0269 0.2422 5.0026 0.1374 0.1155 0.1156 0.0407 -0.0092 0.3000 0.5412 2.0000 0.2836 -0.5475 0.3264 0.0432 0.2353 8.5560 0.1274 0.1032 0.1214 0.0597 -0.0034 0.3750 0.5199 2.0000 0.5289 -0.4144 0.3302 0.0602 0.2288 12.6525 0.1189 0.0900 0.1275 0.0789 0.0030 0.4500 0.5056 2.0000 0.8565 -0.1165 0.3345 0.0765 0.2225 16.8536 0.1125 0.0773 0.1335 0.0967 0.0096 0.5250 0.4989 2.0000 1.2405 0.3249 0.3389 0.0904 0.2165 20.6097 0.1080 0.0662 0.1388 0.1118 0.0160 0.6000 0.4996 2.0000 1.6271 0.8392 0.3431 0.1002 0.2107 23.3457 0.1053 0.0574 0.1425 0.1227 0.0214 0.6750 0.5069 2.0000 1.9377 1.3061 0.3466 0.1043 0.2052 24.5552 0.1040 0.0515 0.1432 0.1277 0.0252 0.7500 0.5207 2.0000 2.0847 1.5756 0.3490 0.1011 0.2000 23.8635 0.1041 0.0491 0.1400 0.1248 0.0259 0.8243 0.5368 2.0000 2.1000 1.6579 0.3504 0.0932 0.1951 22.0707 0.1047 0.0490 0.1340 0.1169 0.0243 0.8866 0.5472 2.0000 2.1113 1.7187 0.3510 0.0869 0.1912 20.7562 0.1046 0.0484 0.1290 0.1115 0.0231 0.9483 0.5546 2.0000 2.1221 1.7728 0.3512 0.0812 0.1875 19.6044 0.1040 0.0476 0.1241 0.1073 0.0220 1.0099 0.5591 2.0000 2.1326 1.8211 0.3509 0.0758 0.1840 18.5769 0.1029 0.0464 0.1193 0.1041 0.0211 1.0716 0.5608 2.0000 2.1429 1.8635 0.3502 0.0707 0.1807 17.6551 0.1013 0.0450 0.1146 0.1020 0.0202 1.1332 0.5596 2.0000 2.1529 1.9001 0.3490 0.0660 0.1776 16.8241 0.0994 0.0434 0.1099 0.1009 0.0194 1.1948 0.5555 2.0000 2.1629 1.9310 0.3475 0.0616 0.1746 16.0717 0.0970 0.0415 0.1053 0.1008 0.0188 1.2565 0.5485 2.0000 2.1727 1.9562 0.3455 0.0576 0.1719 15.3875 0.0943 0.0394 0.1008 0.1016 0.0182 1.3181 0.5388 2.0000 2.1825 1.9756 0.3431 0.0538 0.1693 14.7634 0.0912 0.0371 0.0963 0.1034 0.0177 1.3797 0.5282 2.0000 2.1925 1.9894 0.3403 0.0503 0.1667 14.1929 0.0881 0.0349 0.0919 0.1053 0.0171 1.4414 0.5174 2.0000 2.2026 1.9975 0.3371 0.0469 0.1642 13.6694 0.0849 0.0328 0.0876 0.1070 0.0163 1.5030 0.5063 2.0000 2.2125 2.0000 0.3336 0.0437 0.1616 13.1859 0.0818 0.0309 0.0833 0.1085 0.0154 1.5647 0.4949 2.0000 2.2222 2.0000 0.3296 0.0405 0.1591 12.7373 0.0787 0.0290 0.0791 0.1097 0.0144 1.6263 0.4834 2.0000 2.2316 2.0000 0.3253 0.0375 0.1565 12.3198 0.0756 0.0272 0.0750 0.1107 0.0133 1.6879 0.4715 2.0000 2.2407 2.0000 0.3206 0.0347 0.1540 11.9298 0.0726 0.0254 0.0709 0.1114 0.0122 1.7496 0.4595 2.0000 2.2494 2.0000 0.3155 0.0319 0.1514 11.5643 0.0696 0.0237 0.0669 0.1118 0.0110 1.8112 0.4472 2.0000 2.2576 2.0000 0.3101 0.0292 0.1489 11.2206 0.0666 0.0220 0.0630 0.1120 0.0098 1.8728 0.4346 2.0000 2.2653 2.0000 0.3044 0.0266 0.1463 10.8964 0.0636 0.0204 0.0591 0.1119 0.0086 1.9345 0.4219 2.0000 2.2724 2.0000 0.2983 0.0241 0.1438 10.5894 0.0606 0.0189 0.0553 0.1116 0.0074 1.9961 0.4088 2.0000 2.2788 2.0000 0.2918 0.0217 0.1412 10.2978 0.0577 0.0174 0.0516 0.1110 0.0062 2.0578 0.3956 2.0000 2.2844 1.9953 0.2850 0.0194 0.1386 10.0199 0.0548 0.0160 0.0478 0.1102 0.0049 2.1194 0.3820 2.0000 2.2908 1.9812 0.2779 0.0172 0.1361 9.7609 0.0520 0.0146 0.0441 0.1091 0.0035 2.1810 0.3683 2.0000 2.3010 1.9607 0.2705 0.0152 0.1335 9.5315 0.0492 0.0133 0.0404 0.1078 0.0021 2.2427 0.3544 2.0000 2.3178 1.9366 0.2628 0.0135 0.1310 9.3406 0.0464 0.0121 0.0368 0.1062 0.0007 2.3043 0.3402 2.0000 2.3441 1.9120 0.2548 0.0120 0.1284 9.1965 0.0437 0.0109 0.0334 0.1044 -0.0007 2.3659 0.3259 1.9995 2.3822 1.8896 0.2465 0.0108 0.1259 9.1041 0.0410 0.0098 0.0303 0.1024 -0.0019 2.4276 0.3113 1.9887 2.4248 1.8627 0.2379 0.0098 0.1233 9.0330 0.0384 0.0088 0.0273 0.1001 -0.0030 2.4892 0.2965 1.9637 2.4703 1.8306 0.2290 0.0090 0.1208 8.9756 0.0358 0.0078 0.0246 0.0976 -0.0039 2.5509 0.2815 1.9244 2.5206 1.7962 0.2198 0.0085 0.1182 8.9375 0.0333 0.0069 0.0222 0.0949 -0.0046 2.6100 0.2616 1.8732 2.5754 1.7660 0.2055 0.0073 0.1158 8.9253 0.0303 0.0059 0.0190 0.0892 -0.0057 2.6264 0.2524 1.8568 2.5923 1.7629 0.1979 0.0064 0.1151 8.9275 0.0291 0.0054 0.0174 0.0855 -0.0064 2.6403 0.2429 1.8420 2.6070 1.7624 0.1898 0.0054 0.1145 8.9310 0.0278 0.0050 0.0158 0.0816 -0.0071 2.6542 0.2318 1.8265 2.6221 1.7646 0.1801 0.0042 0.1140 8.9357 0.0264 0.0045 0.0138 0.0766 -0.0080 2.6681 0.2185 1.8103 2.6376 1.7711 0.1682 0.0026 0.1134 8.9415 0.0248 0.0040 0.0115 0.0706 -0.0091 2.6819 0.2025 1.7934 2.6533 1.7837 0.1536 0.0006 0.1128 8.9482 0.0228 0.0034 0.0087 0.0630 -0.0104 2.6958 0.1826 1.7757 2.6694 1.8073 0.1353 -0.0020 0.1122 8.9557 0.0205 0.0028 0.0051 0.0533 -0.0121 2.7097 0.1563 1.7574 2.6860 1.8554 0.1105 -0.0056 0.1117 8.9651 0.0175 0.0020 0.0003 0.0401 -0.0145 2.7236 0.1137 1.7383 2.7038 1.9955 0.0697 -0.0118 0.1111 8.9783 0.0126 0.0011 -0.0076 0.0180 -0.0184 2.7375 0.0600 1.7185 2.7220 2.4669 0.0179 -0.0197 0.1105 8.9927 0.0066 0.0003 -0.0175 -0.0102 -0.0234 2.7500 0.0115 1.7000 1.7000 1.7000 -0.0288 -0.0275 0.1100 5.6191 0.0013 0.0000 -0.0275 0.0000 0.0000 RADIUS: 2.75 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) = 0.014567 TOTAL WEIGHT (Kg) = 0.006607 TOTAL VOLUME (IN**3) = 0.237321 TOTAL PROJECTED AREA (IN**2) = 2.4683 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000039 MOMENT OF INERTIA (Kg-M**2) = 0.000004 STATIC MOMENT, ONE SIDE (IN-LB) = 0.005691 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 = 101.015 INNER LIMIT (NORMALIZED BY RADIUS) = 0.118 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 36787.03 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.00, CLARK-Y (Transition Start, Airfoil 1) AIRFOIL2: 2.00, CLARK-Y (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.