5.1x4.5E (51x45E.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 0.5000 4.5000 0.0000 0.0000 0.2500 0.0000 0.1013 0.0000 0.0507 0.0000 0.0500 0.0000 0.0000 0.0750 0.4749 4.5000 0.0097 -0.3498 0.2455 0.0041 0.0959 1.1765 0.0455 0.0940 0.0527 0.0057 -0.0598 0.1500 0.4474 4.5000 0.0767 -0.6885 0.2400 0.0154 0.0907 4.6539 0.0406 0.0913 0.0603 0.0147 -0.0575 0.2250 0.4228 4.5000 0.2570 -0.9648 0.2342 0.0323 0.0858 10.3038 0.0363 0.0887 0.0712 0.0239 -0.0538 0.3000 0.4069 4.5000 0.6024 -1.0228 0.2289 0.0530 0.0812 17.7222 0.0330 0.0808 0.0813 0.0333 -0.0487 0.3750 0.4041 4.5000 1.1478 -0.7218 0.2248 0.0762 0.0769 25.9719 0.0311 0.0695 0.0933 0.0421 -0.0424 0.4500 0.4156 4.5000 1.8888 0.0060 0.2225 0.1001 0.0729 33.7443 0.0303 0.0573 0.1093 0.0499 -0.0349 0.5250 0.4391 4.5000 2.7553 1.1093 0.2227 0.1234 0.0691 39.8714 0.0303 0.0462 0.1280 0.0560 -0.0260 0.6000 0.4703 4.5000 3.6009 2.3736 0.2259 0.1443 0.0656 43.6865 0.0308 0.0373 0.1469 0.0603 -0.0157 0.6750 0.5048 4.5000 4.2354 3.4476 0.2329 0.1614 0.0624 44.9611 0.0315 0.0314 0.1632 0.0622 -0.0044 0.7500 0.5404 4.5000 4.4978 3.9470 0.2443 0.1731 0.0595 43.6651 0.0321 0.0298 0.1750 0.0602 0.0061 0.8240 0.5744 4.5000 4.5000 4.0202 0.2576 0.1796 0.0568 40.9976 0.0326 0.0314 0.1818 0.0545 0.0137 0.8801 0.5976 4.5000 4.5000 4.0719 0.2665 0.1822 0.0550 39.1380 0.0329 0.0323 0.1847 0.0500 0.0183 0.9352 0.6180 4.5000 4.5000 4.1214 0.2744 0.1830 0.0534 37.4465 0.0330 0.0328 0.1858 0.0456 0.0216 0.9903 0.6363 4.5000 4.5000 4.1685 0.2813 0.1820 0.0519 35.8761 0.0331 0.0330 0.1851 0.0412 0.0237 1.0453 0.6522 4.5000 4.5000 4.2126 0.2872 0.1792 0.0506 34.4162 0.0330 0.0330 0.1825 0.0369 0.0244 1.1004 0.6659 4.5000 4.5000 4.2532 0.2922 0.1747 0.0495 33.0574 0.0329 0.0327 0.1783 0.0326 0.0239 1.1555 0.6774 4.5000 4.5000 4.2902 0.2963 0.1696 0.0484 31.7909 0.0328 0.0321 0.1736 0.0285 0.0231 1.2106 0.6865 4.5000 4.5000 4.3236 0.2994 0.1644 0.0476 30.6087 0.0327 0.0315 0.1686 0.0245 0.0225 1.2657 0.6934 4.5000 4.5000 4.3536 0.3015 0.1590 0.0469 29.5036 0.0325 0.0306 0.1635 0.0207 0.0219 1.3208 0.6980 4.5000 4.5000 4.3803 0.3027 0.1535 0.0463 28.4690 0.0323 0.0296 0.1582 0.0171 0.0213 1.3759 0.7003 4.5000 4.5000 4.4044 0.3030 0.1477 0.0459 27.4990 0.0321 0.0286 0.1527 0.0136 0.0207 1.4309 0.7003 4.5000 4.5000 4.4261 0.3023 0.1417 0.0456 26.5882 0.0319 0.0274 0.1470 0.0104 0.0199 1.4860 0.6980 4.5000 4.5000 4.4455 0.3006 0.1356 0.0455 25.7318 0.0318 0.0262 0.1412 0.0073 0.0191 1.5411 0.6934 4.5000 4.5000 4.4628 0.2980 0.1292 0.0455 24.9255 0.0316 0.0250 0.1351 0.0044 0.0181 1.5962 0.6865 4.5000 4.5000 4.4783 0.2944 0.1227 0.0455 24.1652 0.0312 0.0237 0.1289 0.0018 0.0170 1.6513 0.6772 4.5000 4.5000 4.4929 0.2899 0.1161 0.0455 23.4473 0.0308 0.0223 0.1225 -0.0008 0.0158 1.7064 0.6656 4.5000 4.5000 4.5069 0.2844 0.1093 0.0455 22.7686 0.0303 0.0209 0.1158 -0.0031 0.0143 1.7615 0.6517 4.5000 4.5000 4.5201 0.2780 0.1023 0.0455 22.1262 0.0297 0.0195 0.1090 -0.0054 0.0127 1.8166 0.6354 4.5000 4.5000 4.5332 0.2706 0.0952 0.0455 21.5174 0.0289 0.0180 0.1021 -0.0075 0.0109 1.8716 0.6167 4.5000 4.5000 4.5461 0.2623 0.0880 0.0455 20.9397 0.0281 0.0166 0.0949 -0.0094 0.0089 1.9267 0.5957 4.5000 4.5000 4.5589 0.2530 0.0806 0.0455 20.3910 0.0271 0.0152 0.0876 -0.0112 0.0066 1.9818 0.5723 4.5000 4.5000 4.5720 0.2428 0.0731 0.0455 19.8691 0.0260 0.0138 0.0800 -0.0129 0.0042 2.0369 0.5466 4.5000 4.5000 4.5852 0.2316 0.0655 0.0455 19.3723 0.0249 0.0124 0.0723 -0.0144 0.0016 2.0920 0.5184 4.5000 4.5000 4.5980 0.2195 0.0577 0.0455 18.8988 0.0236 0.0110 0.0644 -0.0158 -0.0013 2.1471 0.4879 4.5000 4.5000 4.6125 0.2064 0.0498 0.0455 18.4471 0.0222 0.0096 0.0563 -0.0170 -0.0043 2.2022 0.4550 4.5000 4.5000 4.6287 0.1924 0.0418 0.0455 18.0159 0.0207 0.0083 0.0480 -0.0181 -0.0076 2.2572 0.4197 4.5000 4.5000 4.6484 0.1774 0.0336 0.0455 17.6036 0.0191 0.0071 0.0396 -0.0190 -0.0110 2.3123 0.3819 4.5000 4.5000 4.6719 0.1615 0.0254 0.0455 17.2093 0.0174 0.0059 0.0309 -0.0198 -0.0147 2.3674 0.3418 4.5000 4.5000 4.7017 0.1446 0.0170 0.0455 16.8318 0.0156 0.0048 0.0221 -0.0203 -0.0185 2.4203 0.3009 4.5000 4.5000 4.7398 0.1275 0.0088 0.0455 16.4842 0.0137 0.0038 0.0134 -0.0204 -0.0223 2.4354 0.2889 4.5000 4.5000 4.7524 0.1224 0.0065 0.0455 16.3876 0.0131 0.0035 0.0109 -0.0204 -0.0234 2.4483 0.2785 4.5000 4.5000 4.7644 0.1181 0.0044 0.0455 16.3060 0.0127 0.0033 0.0088 -0.0204 -0.0243 2.4611 0.2678 4.5000 4.5000 4.7775 0.1136 0.0024 0.0455 16.2251 0.0122 0.0031 0.0066 -0.0203 -0.0253 2.4740 0.2558 4.5000 4.5000 4.7920 0.1080 0.0000 0.0455 16.1451 0.0116 0.0028 0.0041 -0.0207 -0.0265 2.4869 0.2404 4.5000 4.5000 4.8082 0.1006 -0.0028 0.0455 16.0658 0.0109 0.0025 0.0010 -0.0210 -0.0278 2.4998 0.2208 4.5000 4.5000 4.8258 0.0913 -0.0062 0.0455 15.9873 0.0100 0.0021 -0.0027 -0.0212 -0.0292 2.5127 0.1957 4.5000 4.5000 4.8476 0.0793 -0.0102 0.0455 15.9095 0.0089 0.0015 -0.0072 -0.0213 -0.0308 2.5255 0.1626 4.5000 4.5000 4.9372 0.0634 -0.0155 0.0455 15.8324 0.0074 0.0011 -0.0129 -0.0208 -0.0327 2.5384 0.1147 4.5000 4.5000 5.1646 0.0403 -0.0226 0.0455 15.7561 0.0052 0.0006 -0.0208 -0.0211 -0.0355 2.5500 0.0038 4.5000 4.5023 4.5023 -0.0130 -0.0383 0.0455 15.6956 0.0002 0.0000 -0.0383 0.0000 0.0000 RADIUS: 2.55 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.75 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.010552 TOTAL WEIGHT (Kg) = 0.004785 TOTAL VOLUME (IN**3) = 0.171906 TOTAL PROJECTED AREA (IN**2) = 2.4109 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000027 MOMENT OF INERTIA (Kg-M**2) = 0.000003 STATIC MOMENT, ONE SIDE (IN-LB) = 0.004042 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 = 146.282 INNER LIMIT (NORMALIZED BY RADIUS) = 0.098 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 27822.61 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.00, E63 (Transition Start, Airfoil 1) AIRFOIL2: 2.00, E63 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.