8x4.1SF (8x41SF.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 0.3755 0.0000 0.0000 0.2500 0.0000 0.1156 0.0000 0.0578 0.0000 0.0450 0.0000 0.0000 0.0700 0.4935 0.6603 0.0079 -0.0759 0.2483 0.0046 0.1087 1.0301 0.0537 0.0401 0.0484 0.0016 0.0002 0.1400 0.4893 0.9323 0.0595 -0.1338 0.2499 0.0171 0.1024 3.8691 0.0501 0.0452 0.0572 0.0059 0.0009 0.2100 0.4894 1.1917 0.1871 -0.1048 0.2543 0.0354 0.0964 8.0713 0.0472 0.0469 0.0681 0.0128 0.0035 0.2800 0.4961 1.4388 0.4089 0.0634 0.2612 0.0577 0.0910 13.0833 0.0451 0.0455 0.0819 0.0214 0.0075 0.3500 0.5102 1.6737 0.7265 0.3918 0.2700 0.0821 0.0859 18.2822 0.0438 0.0420 0.0988 0.0311 0.0129 0.4200 0.5315 1.8966 1.1245 0.8621 0.2802 0.1066 0.0813 23.0790 0.0432 0.0372 0.1179 0.0414 0.0193 0.4900 0.5580 2.1078 1.5699 1.4002 0.2916 0.1296 0.0770 27.0175 0.0430 0.0319 0.1373 0.0518 0.0266 0.5600 0.5870 2.3075 2.0154 1.9399 0.3035 0.1490 0.0731 29.8037 0.0429 0.0267 0.1545 0.0617 0.0344 0.6300 0.6156 2.4958 2.4034 2.3970 0.3155 0.1631 0.0696 31.2648 0.0429 0.0226 0.1675 0.0701 0.0418 0.7000 0.6414 2.6730 2.6722 2.6946 0.3272 0.1699 0.0665 31.2811 0.0426 0.0205 0.1741 0.0742 0.0466 0.7718 0.6648 2.8435 2.8435 2.8767 0.3385 0.1714 0.0635 30.3856 0.0422 0.0202 0.1760 0.0737 0.0484 0.8745 0.6959 3.0677 3.0677 3.1066 0.3528 0.1727 0.0599 29.1751 0.0417 0.0204 0.1777 0.0727 0.0501 0.9790 0.7240 3.2728 3.2728 3.3124 0.3654 0.1730 0.0569 28.0164 0.0412 0.0211 0.1785 0.0713 0.0513 1.0834 0.7471 3.4555 3.4555 3.4957 0.3759 0.1723 0.0544 26.9121 0.0406 0.0216 0.1783 0.0700 0.0524 1.1879 0.7653 3.6163 3.6163 3.6571 0.3846 0.1706 0.0524 25.8501 0.0401 0.0220 0.1772 0.0688 0.0536 1.2924 0.7790 3.7560 3.7560 3.7974 0.3913 0.1681 0.0509 24.8221 0.0397 0.0222 0.1752 0.0676 0.0546 1.3969 0.7884 3.8752 3.8752 3.9173 0.3962 0.1648 0.0499 23.8226 0.0393 0.0223 0.1724 0.0666 0.0556 1.5014 0.7937 3.9747 3.9747 4.0175 0.3992 0.1607 0.0491 22.8478 0.0390 0.0224 0.1688 0.0655 0.0563 1.6059 0.7952 4.0551 4.0551 4.0988 0.4006 0.1558 0.0487 21.8951 0.0387 0.0223 0.1644 0.0645 0.0568 1.7103 0.7932 4.1172 4.1172 4.1618 0.4001 0.1502 0.0485 20.9628 0.0385 0.0221 0.1594 0.0634 0.0569 1.8148 0.7880 4.1615 4.1615 4.2073 0.3981 0.1439 0.0485 20.0494 0.0382 0.0218 0.1536 0.0621 0.0566 1.9193 0.7797 4.1888 4.1888 4.2359 0.3944 0.1371 0.0485 19.1544 0.0378 0.0214 0.1473 0.0605 0.0558 2.0238 0.7686 4.1997 4.1997 4.2485 0.3891 0.1297 0.0486 18.2770 0.0373 0.0208 0.1404 0.0586 0.0545 2.1283 0.7551 4.2000 4.2000 4.2508 0.3823 0.1217 0.0486 17.4365 0.0367 0.0201 0.1330 0.0563 0.0526 2.2328 0.7392 4.2000 4.2000 4.2532 0.3741 0.1134 0.0486 16.6668 0.0359 0.0193 0.1251 0.0536 0.0498 2.3372 0.7214 4.2000 4.2000 4.2561 0.3644 0.1046 0.0486 15.9605 0.0351 0.0184 0.1167 0.0503 0.0463 2.4417 0.7019 4.2000 4.2000 4.2596 0.3533 0.0956 0.0486 15.3103 0.0341 0.0175 0.1079 0.0466 0.0421 2.5462 0.6809 4.2000 4.2000 4.2636 0.3409 0.0862 0.0487 14.7098 0.0331 0.0165 0.0988 0.0421 0.0372 2.6507 0.6586 4.2000 4.2000 4.2682 0.3271 0.0766 0.0487 14.1537 0.0321 0.0155 0.0894 0.0370 0.0318 2.7552 0.6354 4.2000 4.2000 4.2736 0.3122 0.0667 0.0487 13.6374 0.0310 0.0145 0.0796 0.0311 0.0259 2.8597 0.6115 4.2000 4.2000 4.2797 0.2960 0.0567 0.0487 13.1568 0.0298 0.0135 0.0697 0.0244 0.0195 2.9641 0.5871 4.2000 4.2000 4.2862 0.2787 0.0466 0.0488 12.7083 0.0286 0.0125 0.0595 0.0168 0.0127 3.0686 0.5625 4.2000 4.2000 4.2935 0.2603 0.0364 0.0488 12.2890 0.0274 0.0115 0.0492 0.0082 0.0055 3.1731 0.5380 4.2000 4.2000 4.3017 0.2409 0.0261 0.0488 11.8961 0.0263 0.0106 0.0388 -0.0015 -0.0020 3.2776 0.5138 4.2000 4.2000 4.3109 0.2204 0.0159 0.0488 11.5272 0.0251 0.0097 0.0284 -0.0122 -0.0097 3.3821 0.4902 4.1984 4.1984 4.3195 0.1990 0.0056 0.0489 11.1759 0.0240 0.0089 0.0179 -0.0240 -0.0176 3.4866 0.4674 4.1841 4.1841 4.3156 0.1766 -0.0047 0.0489 10.8131 0.0228 0.0082 0.0075 -0.0371 -0.0257 3.5910 0.4456 4.1551 4.1551 4.2977 0.1534 -0.0149 0.0489 10.4344 0.0218 0.0075 -0.0029 -0.0515 -0.0338 3.6955 0.4241 4.1114 4.1114 4.2657 0.1282 -0.0253 0.0489 10.0410 0.0208 0.0068 -0.0135 -0.0678 -0.0420 3.7956 0.3831 4.0557 4.0557 4.2217 0.0818 -0.0387 0.0490 9.6514 0.0188 0.0056 -0.0277 -0.0961 -0.0528 3.8202 0.3677 4.0399 4.0399 4.2122 0.0648 -0.0429 0.0490 9.5539 0.0180 0.0052 -0.0322 -0.1062 -0.0562 3.8404 0.3532 4.0264 4.0264 4.2102 0.0489 -0.0466 0.0490 9.4733 0.0173 0.0048 -0.0362 -0.1158 -0.0592 3.8606 0.3364 4.0123 4.0123 4.2105 0.0307 -0.0506 0.0490 9.3922 0.0165 0.0044 -0.0407 -0.1267 -0.0625 3.8808 0.3172 3.9976 3.9976 4.2143 0.0098 -0.0550 0.0490 9.3106 0.0155 0.0039 -0.0456 -0.1390 -0.0662 3.9010 0.2947 3.9824 3.9824 4.2237 -0.0142 -0.0599 0.0490 9.2286 0.0144 0.0034 -0.0511 -0.1532 -0.0702 3.9212 0.2680 3.9667 3.9667 4.2292 -0.0426 -0.0656 0.0490 9.1462 0.0131 0.0029 -0.0574 -0.1711 -0.0753 3.9414 0.2352 3.9504 3.9504 4.2270 -0.0772 -0.0723 0.0490 9.0633 0.0115 0.0025 -0.0649 -0.1933 -0.0819 3.9616 0.1918 3.9335 3.9335 4.2646 -0.1223 -0.0802 0.0490 8.9800 0.0094 0.0016 -0.0742 -0.2202 -0.0892 3.9818 0.1208 3.9161 3.9161 4.5301 -0.1948 -0.0922 0.0490 8.8963 0.0059 0.0006 -0.0884 -0.2598 -0.0988 4.0000 0.0188 3.9000 3.9038 3.9038 -0.2978 -0.1087 0.0490 8.8290 0.0009 0.0000 -0.1087 0.0000 0.0000 RADIUS: 4.01 PROPELLER RADIUS (IN) HUBRAD: 0.25 HUB RADIUS (IN) HUBTRA: 0.70 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.009608 TOTAL WEIGHT (Kg) = 0.004357 TOTAL VOLUME (IN**3) = 0.156528 TOTAL PROJECTED AREA (IN**2) = 4.6789 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000080 MOMENT OF INERTIA (Kg-M**2) = 0.000009 STATIC MOMENT, ONE SIDE (IN-LB) = 0.006986 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 = 102.549 INNER LIMIT (NORMALIZED BY RADIUS) = 0.062 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 5589.96 BASED ON MODULUS (MILLION) = 1.60 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 3.90, E63 (Transition Start, Airfoil 1) AIRFOIL2: 4.00, APC12 (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE. NOTE: APC12 airfoil is equivalent to NACA 4412