5x4.1SF (5x41SF.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 0.0781 0.0000 0.0000 0.2500 0.0000 0.1128 0.0000 0.0564 0.0000 0.0450 0.0000 0.0000 0.0550 0.4893 0.5000 0.0054 -0.0593 0.2462 0.0041 0.1064 0.9022 0.0520 0.0393 0.0479 0.0016 0.0002 0.1100 0.4706 0.8924 0.0422 -0.1141 0.2408 0.0154 0.1006 3.4925 0.0473 0.0430 0.0557 0.0060 0.0009 0.1650 0.4482 1.2563 0.1394 -0.1197 0.2346 0.0318 0.0954 7.6575 0.0428 0.0435 0.0652 0.0126 0.0030 0.2200 0.4268 1.5927 0.3250 -0.0104 0.2281 0.0517 0.0908 13.2300 0.0388 0.0398 0.0759 0.0206 0.0065 0.2750 0.4106 1.9026 0.6233 0.2665 0.2221 0.0734 0.0868 19.8371 0.0356 0.0338 0.0889 0.0295 0.0111 0.3300 0.4023 2.1871 1.0478 0.7463 0.2171 0.0952 0.0832 26.8101 0.0335 0.0271 0.1043 0.0384 0.0161 0.3850 0.4027 2.4470 1.5867 1.3875 0.2138 0.1153 0.0802 33.2619 0.0323 0.0207 0.1204 0.0468 0.0212 0.4400 0.4101 2.6836 2.1848 2.1145 0.2127 0.1322 0.0776 38.3179 0.0318 0.0155 0.1350 0.0539 0.0260 0.4950 0.4220 2.8976 2.7332 2.7664 0.2145 0.1441 0.0754 41.3090 0.0318 0.0119 0.1460 0.0592 0.0300 0.5500 0.4359 3.0902 3.0887 3.1605 0.2199 0.1493 0.0736 41.7897 0.0321 0.0104 0.1510 0.0615 0.0320 0.6053 0.4498 3.2633 3.2633 3.3417 0.2272 0.1496 0.0721 40.6303 0.0324 0.0105 0.1515 0.0613 0.0325 0.6660 0.4627 3.4307 3.4307 3.5095 0.2342 0.1494 0.0709 39.3450 0.0328 0.0108 0.1515 0.0611 0.0332 0.7271 0.4734 3.5765 3.5765 3.6540 0.2399 0.1487 0.0699 38.0572 0.0331 0.0111 0.1509 0.0606 0.0341 0.7881 0.4819 3.7011 3.7011 3.7774 0.2444 0.1475 0.0693 36.7753 0.0334 0.0114 0.1499 0.0598 0.0352 0.8491 0.4882 3.8059 3.8059 3.8812 0.2479 0.1458 0.0688 35.5017 0.0336 0.0116 0.1485 0.0586 0.0365 0.9102 0.4925 3.8922 3.8922 3.9666 0.2502 0.1437 0.0686 34.2391 0.0338 0.0118 0.1465 0.0572 0.0378 0.9712 0.4948 3.9615 3.9615 4.0351 0.2514 0.1412 0.0685 32.9908 0.0339 0.0118 0.1442 0.0554 0.0392 1.0322 0.4954 4.0150 4.0150 4.0882 0.2516 0.1383 0.0685 31.7598 0.0339 0.0118 0.1415 0.0534 0.0404 1.0933 0.4942 4.0543 4.0543 4.1272 0.2508 0.1349 0.0685 30.5496 0.0338 0.0118 0.1384 0.0512 0.0416 1.1543 0.4914 4.0807 4.0807 4.1536 0.2491 0.1312 0.0685 29.3636 0.0337 0.0116 0.1349 0.0488 0.0425 1.2153 0.4871 4.0954 4.0954 4.1687 0.2464 0.1271 0.0685 28.2053 0.0334 0.0114 0.1311 0.0461 0.0433 1.2764 0.4813 4.1000 4.1000 4.1740 0.2429 0.1227 0.0686 27.0779 0.0330 0.0112 0.1270 0.0433 0.0437 1.3374 0.4743 4.1000 4.1000 4.1752 0.2385 0.1180 0.0686 26.0081 0.0325 0.0109 0.1226 0.0402 0.0438 1.3984 0.4660 4.1000 4.1000 4.1768 0.2332 0.1131 0.0686 25.0144 0.0320 0.0105 0.1180 0.0372 0.0435 1.4595 0.4566 4.1000 4.1000 4.1789 0.2273 0.1080 0.0686 24.0894 0.0313 0.0101 0.1131 0.0338 0.0428 1.5205 0.4463 4.1000 4.1000 4.1815 0.2205 0.1027 0.0686 23.2268 0.0306 0.0097 0.1079 0.0302 0.0417 1.5816 0.4350 4.1000 4.1000 4.1846 0.2131 0.0972 0.0687 22.4206 0.0299 0.0092 0.1026 0.0265 0.0402 1.6426 0.4229 4.1000 4.1000 4.1883 0.2050 0.0915 0.0687 21.6660 0.0290 0.0087 0.0971 0.0225 0.0384 1.7036 0.4101 4.1000 4.1000 4.1926 0.1963 0.0858 0.0687 20.9583 0.0282 0.0082 0.0915 0.0182 0.0362 1.7647 0.3967 4.1000 4.1000 4.1975 0.1869 0.0799 0.0687 20.2934 0.0273 0.0077 0.0857 0.0136 0.0338 1.8257 0.3829 4.1000 4.1000 4.2031 0.1770 0.0740 0.0688 19.6678 0.0263 0.0072 0.0798 0.0088 0.0311 1.8867 0.3686 4.1000 4.1000 4.2093 0.1666 0.0679 0.0688 19.0783 0.0254 0.0067 0.0738 0.0037 0.0281 1.9478 0.3541 4.1000 4.1000 4.2163 0.1557 0.0619 0.0688 18.5218 0.0244 0.0063 0.0678 -0.0017 0.0249 2.0088 0.3394 4.1000 4.1000 4.2240 0.1444 0.0558 0.0688 17.9958 0.0234 0.0058 0.0617 -0.0074 0.0216 2.0698 0.3245 4.1000 4.1000 4.2295 0.1327 0.0497 0.0688 17.4980 0.0223 0.0053 0.0556 -0.0132 0.0181 2.1309 0.3097 4.0959 4.0959 4.2256 0.1205 0.0436 0.0689 17.0101 0.0213 0.0048 0.0495 -0.0188 0.0147 2.1919 0.2951 4.0792 4.0792 4.2032 0.1081 0.0375 0.0689 16.4989 0.0203 0.0044 0.0434 -0.0244 0.0113 2.2529 0.2806 4.0497 4.0497 4.1603 0.0953 0.0315 0.0689 15.9650 0.0193 0.0039 0.0373 -0.0298 0.0081 2.3140 0.2662 4.0073 4.0073 4.0951 0.0820 0.0254 0.0689 15.4096 0.0183 0.0034 0.0313 -0.0352 0.0048 2.3725 0.2410 3.9547 3.9547 4.0103 0.0577 0.0166 0.0690 14.8581 0.0166 0.0028 0.0222 -0.0466 -0.0005 2.3876 0.2313 3.9392 3.9392 3.9845 0.0481 0.0135 0.0690 14.7124 0.0159 0.0025 0.0190 -0.0513 -0.0024 2.4003 0.2219 3.9256 3.9256 3.9617 0.0389 0.0107 0.0690 14.5901 0.0153 0.0023 0.0160 -0.0559 -0.0043 2.4129 0.2111 3.9115 3.9115 3.9406 0.0283 0.0075 0.0690 14.4670 0.0146 0.0021 0.0127 -0.0614 -0.0064 2.4255 0.1988 3.8968 3.8968 3.9194 0.0162 0.0039 0.0690 14.3431 0.0137 0.0018 0.0089 -0.0680 -0.0089 2.4381 0.1844 3.8816 3.8816 3.8845 0.0020 -0.0002 0.0690 14.2184 0.0127 0.0016 0.0046 -0.0767 -0.0123 2.4508 0.1674 3.8658 3.8658 3.8367 -0.0147 -0.0052 0.0690 14.0930 0.0115 0.0014 -0.0005 -0.0874 -0.0165 2.4634 0.1467 3.8495 3.8495 3.7863 -0.0352 -0.0110 0.0690 13.9667 0.0101 0.0012 -0.0066 -0.1002 -0.0215 2.4760 0.1196 3.8327 3.8327 3.7420 -0.0618 -0.0182 0.0690 13.8398 0.0083 0.0008 -0.0144 -0.1157 -0.0272 2.4886 0.0767 3.8153 3.8153 3.7326 -0.1039 -0.0290 0.0690 13.7120 0.0053 0.0003 -0.0264 -0.1389 -0.0349 2.5000 0.0113 3.7991 3.8029 3.8029 -0.1678 -0.0446 0.0690 13.6093 0.0008 0.0000 -0.0446 0.0000 0.0000 RADIUS: 2.50 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.55 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.004016 TOTAL WEIGHT (Kg) = 0.001821 TOTAL VOLUME (IN**3) = 0.065429 TOTAL PROJECTED AREA (IN**2) = 1.8240 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000011 MOMENT OF INERTIA (Kg-M**2) = 0.000001 STATIC MOMENT, ONE SIDE (IN-LB) = 0.001550 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 = 104.343 INNER LIMIT (NORMALIZED BY RADIUS) = 0.100 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 12123.51 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 2.42, E63 (Transition Start, Airfoil 1) AIRFOIL2: 2.50, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412