5x5E (5x5E.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 5.0000 0.0000 0.0000 0.2500 0.0000 0.1500 0.0000 0.0750 0.0000 0.0500 0.0000 0.0000 0.0660 0.4780 5.0000 0.0111 -0.1650 0.2467 0.0088 0.1487 1.5325 0.0711 0.0635 0.0574 0.0064 -0.0196 0.1320 0.4546 5.0000 0.0866 -0.3162 0.2433 0.0324 0.1475 5.9592 0.0670 0.0675 0.0768 0.0160 -0.0114 0.1980 0.4357 5.0000 0.2848 -0.3695 0.2402 0.0667 0.1462 12.8957 0.0637 0.0678 0.1028 0.0273 0.0013 0.2640 0.4273 5.0000 0.6560 -0.2354 0.2373 0.1079 0.1449 21.5762 0.0619 0.0647 0.1338 0.0393 0.0175 0.3300 0.4325 5.0000 1.2332 0.1573 0.2348 0.1521 0.1437 30.7419 0.0621 0.0595 0.1688 0.0509 0.0363 0.3960 0.4502 5.0000 2.0162 0.8460 0.2329 0.1957 0.1424 39.0189 0.0641 0.0532 0.2054 0.0614 0.0565 0.4620 0.4749 5.0000 2.9483 1.8043 0.2317 0.2349 0.1412 45.4456 0.0670 0.0468 0.2400 0.0700 0.0767 0.5280 0.4993 5.0000 3.8969 2.9054 0.2312 0.2658 0.1399 49.5914 0.0698 0.0408 0.2686 0.0758 0.0957 0.5940 0.5166 5.0000 4.6570 3.8810 0.2317 0.2848 0.1386 51.2905 0.0716 0.0355 0.2866 0.0783 0.1115 0.6600 0.5217 5.0000 4.9969 4.4569 0.2332 0.2881 0.1374 50.3109 0.0717 0.0311 0.2898 0.0763 0.1220 0.7255 0.5172 5.0000 5.0000 4.6439 0.2351 0.2800 0.1361 47.6440 0.0704 0.0274 0.2819 0.0718 0.1271 0.7829 0.5123 5.0000 5.0000 4.7607 0.2365 0.2717 0.1350 45.4686 0.0692 0.0247 0.2738 0.0687 0.1293 0.8397 0.5070 5.0000 5.0000 4.8392 0.2375 0.2624 0.1339 43.4607 0.0679 0.0228 0.2649 0.0661 0.1290 0.8966 0.5014 5.0000 5.0000 4.8798 0.2382 0.2519 0.1328 41.5910 0.0666 0.0217 0.2550 0.0634 0.1256 0.9534 0.4955 5.0000 5.0000 4.8849 0.2385 0.2401 0.1318 39.8493 0.0653 0.0214 0.2441 0.0608 0.1192 1.0103 0.4892 5.0000 5.0000 4.8755 0.2385 0.2270 0.1307 38.2259 0.0639 0.0214 0.2323 0.0582 0.1106 1.0672 0.4825 5.0000 5.0000 4.8675 0.2382 0.2137 0.1296 36.7113 0.0625 0.0213 0.2205 0.0558 0.1015 1.1240 0.4754 5.0000 5.0000 4.8621 0.2375 0.2006 0.1285 35.2971 0.0611 0.0212 0.2088 0.0537 0.0926 1.1809 0.4680 5.0000 5.0000 4.8598 0.2366 0.1880 0.1274 33.9750 0.0596 0.0208 0.1973 0.0520 0.0843 1.2378 0.4602 5.0000 5.0000 4.8605 0.2353 0.1760 0.1263 32.7376 0.0581 0.0202 0.1861 0.0508 0.0770 1.2946 0.4521 5.0000 5.0000 4.8627 0.2337 0.1646 0.1252 31.5781 0.0566 0.0195 0.1751 0.0501 0.0706 1.3515 0.4436 5.0000 5.0000 4.8633 0.2318 0.1537 0.1241 30.4903 0.0551 0.0187 0.1644 0.0498 0.0647 1.4083 0.4347 5.0000 5.0000 4.8640 0.2297 0.1431 0.1230 29.4683 0.0535 0.0178 0.1538 0.0495 0.0589 1.4652 0.4254 5.0000 5.0000 4.8649 0.2272 0.1327 0.1220 28.5070 0.0519 0.0170 0.1435 0.0493 0.0531 1.5221 0.4158 5.0000 5.0000 4.8661 0.2244 0.1226 0.1209 27.6017 0.0503 0.0161 0.1334 0.0491 0.0474 1.5789 0.4059 5.0000 5.0000 4.8676 0.2214 0.1126 0.1198 26.7479 0.0486 0.0153 0.1235 0.0490 0.0417 1.6358 0.3956 5.0000 5.0000 4.8693 0.2181 0.1030 0.1187 25.9418 0.0469 0.0144 0.1138 0.0489 0.0361 1.6927 0.3849 5.0000 5.0000 4.8714 0.2145 0.0935 0.1176 25.1798 0.0453 0.0136 0.1043 0.0487 0.0305 1.7495 0.3738 5.0000 5.0000 4.8740 0.2106 0.0843 0.1165 24.4586 0.0436 0.0127 0.0950 0.0486 0.0250 1.8064 0.3624 5.0000 5.0000 4.8771 0.2064 0.0753 0.1154 23.7752 0.0418 0.0119 0.0860 0.0485 0.0196 1.8632 0.3506 5.0000 5.0000 4.8806 0.2020 0.0666 0.1143 23.1269 0.0401 0.0111 0.0771 0.0483 0.0143 1.9201 0.3385 5.0000 5.0000 4.8848 0.1974 0.0582 0.1132 22.5113 0.0383 0.0103 0.0685 0.0482 0.0091 1.9770 0.3260 5.0000 5.0000 4.8898 0.1924 0.0499 0.1122 21.9259 0.0366 0.0095 0.0601 0.0480 0.0040 2.0338 0.3131 5.0000 5.0000 4.8956 0.1873 0.0420 0.1111 21.3689 0.0348 0.0087 0.0519 0.0478 -0.0010 2.0907 0.2999 5.0000 5.0000 4.9023 0.1818 0.0342 0.1100 20.8382 0.0330 0.0079 0.0439 0.0475 -0.0058 2.1476 0.2863 5.0000 5.0000 4.9102 0.1762 0.0267 0.1089 20.3322 0.0312 0.0072 0.0361 0.0473 -0.0105 2.2044 0.2723 5.0000 5.0000 4.9194 0.1702 0.0195 0.1078 19.8491 0.0294 0.0065 0.0286 0.0470 -0.0150 2.2613 0.2580 5.0000 5.0000 4.9301 0.1641 0.0125 0.1067 19.3877 0.0275 0.0058 0.0212 0.0467 -0.0194 2.3181 0.2433 5.0000 5.0000 4.9428 0.1577 0.0057 0.1056 18.9464 0.0257 0.0052 0.0141 0.0463 -0.0237 2.3727 0.2273 5.0000 5.0000 4.9572 0.1499 -0.0010 0.1046 18.5409 0.0238 0.0045 0.0069 0.0453 -0.0279 2.3876 0.2201 5.0000 5.0000 4.9614 0.1451 -0.0037 0.1043 18.4328 0.0230 0.0042 0.0040 0.0436 -0.0296 2.4003 0.2124 5.0000 5.0000 4.9649 0.1396 -0.0064 0.1041 18.3423 0.0221 0.0039 0.0010 0.0415 -0.0313 2.4129 0.2032 5.0000 5.0000 4.9736 0.1326 -0.0096 0.1038 18.2527 0.0211 0.0036 -0.0025 0.0385 -0.0333 2.4255 0.1921 5.0000 5.0000 4.9907 0.1237 -0.0133 0.1036 18.1639 0.0199 0.0032 -0.0066 0.0346 -0.0357 2.4381 0.1786 5.0000 5.0000 5.0147 0.1127 -0.0178 0.1033 18.0760 0.0185 0.0028 -0.0115 0.0295 -0.0385 2.4508 0.1620 5.0000 5.0000 5.0500 0.0986 -0.0232 0.1031 17.9889 0.0167 0.0023 -0.0174 0.0228 -0.0420 2.4634 0.1402 5.0000 5.0000 5.1094 0.0796 -0.0300 0.1029 17.9026 0.0144 0.0017 -0.0251 0.0136 -0.0464 2.4760 0.1069 5.0000 5.0000 5.2479 0.0497 -0.0404 0.1026 17.8171 0.0110 0.0010 -0.0366 -0.0014 -0.0530 2.4886 0.0558 5.0000 5.0000 5.7813 0.0027 -0.0561 0.1024 17.7324 0.0057 0.0003 -0.0541 -0.0251 -0.0631 2.5000 0.0097 5.0000 5.0025 5.0025 -0.0397 -0.0700 0.1022 17.6651 0.0010 0.0000 -0.0700 0.0000 0.0000 RADIUS: 2.50 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.66 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.007753 TOTAL WEIGHT (Kg) = 0.003516 TOTAL VOLUME (IN**3) = 0.126307 TOTAL PROJECTED AREA (IN**2) = 1.7088 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000018 MOMENT OF INERTIA (Kg-M**2) = 0.000002 STATIC MOMENT, ONE SIDE (IN-LB) = 0.002866 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 = 97.284 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 35059.05 BASED ON MODULUS (MILLION) = 2.80 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 0.80, E63 (Transition Start, Airfoil 1) AIRFOIL2: 1.30, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412