6x3R-RH (6x3R-RH.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 0.4800 0.5564 0.0000 0.0000 0.2400 0.0000 0.1026 0.0000 0.0492 0.0000 0.0900 0.0000 0.0000 0.0550 0.4568 0.7263 0.0083 -0.1308 0.2285 0.0055 0.1008 1.3733 0.0461 0.0711 0.0930 0.0001 0.0000 0.1100 0.4524 0.8889 0.0617 -0.2261 0.2258 0.0200 0.0992 5.1001 0.0449 0.0712 0.0978 0.0005 0.0001 0.1650 0.4658 1.0444 0.1872 -0.2249 0.2300 0.0412 0.0976 10.2351 0.0455 0.0699 0.1028 0.0010 0.0000 0.2200 0.4952 1.1927 0.3880 -0.1042 0.2397 0.0666 0.0961 15.6780 0.0476 0.0672 0.1099 0.0017 -0.0001 0.2750 0.5368 1.3338 0.6484 0.1239 0.2529 0.0938 0.0947 20.5701 0.0508 0.0631 0.1209 0.0024 -0.0002 0.3300 0.5850 1.4677 0.9436 0.4266 0.2682 0.1205 0.0934 24.4705 0.0547 0.0575 0.1356 0.0031 -0.0002 0.3850 0.6337 1.5944 1.2464 0.7627 0.2837 0.1442 0.0922 27.2603 0.0584 0.0510 0.1521 0.0038 -0.0001 0.4400 0.6764 1.7139 1.5303 1.0894 0.2978 0.1626 0.0911 28.9655 0.0616 0.0443 0.1671 0.0042 0.0001 0.4950 0.7070 1.8262 1.7685 1.3627 0.3088 0.1732 0.0901 29.6227 0.0637 0.0387 0.1766 0.0042 0.0002 0.5500 0.7201 1.9314 1.9308 1.5335 0.3150 0.1738 0.0892 29.1934 0.0642 0.0359 0.1770 0.0030 -0.0001 0.6062 0.7200 2.0314 2.0314 1.6146 0.3174 0.1672 0.0883 28.0732 0.0636 0.0353 0.1705 0.0013 -0.0007 0.6824 0.7176 2.1551 2.1551 1.7047 0.3195 0.1583 0.0873 26.6845 0.0627 0.0347 0.1617 0.0001 -0.0016 0.7598 0.7126 2.2665 2.2665 1.7812 0.3204 0.1494 0.0865 25.3961 0.0616 0.0340 0.1529 -0.0006 -0.0023 0.8372 0.7050 2.3638 2.3638 1.8435 0.3199 0.1406 0.0858 24.1961 0.0605 0.0331 0.1441 -0.0009 -0.0030 0.9147 0.6948 2.4467 2.4467 1.8915 0.3182 0.1318 0.0854 23.0617 0.0593 0.0321 0.1354 -0.0009 -0.0035 0.9921 0.6821 2.5155 2.5155 1.9250 0.3151 0.1230 0.0851 21.9768 0.0580 0.0308 0.1266 -0.0007 -0.0039 1.0695 0.6668 2.5700 2.5700 1.9435 0.3108 0.1144 0.0850 20.9296 0.0567 0.0294 0.1181 -0.0002 -0.0040 1.1469 0.6502 2.6109 2.6109 1.9481 0.3052 0.1065 0.0850 19.9159 0.0553 0.0280 0.1102 0.0000 -0.0037 1.2243 0.6335 2.6480 2.6480 1.9489 0.2991 0.0991 0.0850 18.9952 0.0539 0.0266 0.1029 -0.0001 -0.0035 1.3017 0.6169 2.6852 2.6852 1.9493 0.2927 0.0923 0.0850 18.1754 0.0524 0.0252 0.0961 0.0000 -0.0034 1.3791 0.6003 2.7224 2.7224 1.9494 0.2861 0.0860 0.0850 17.4411 0.0510 0.0239 0.0898 0.0001 -0.0035 1.4566 0.5837 2.7596 2.7596 1.9494 0.2793 0.0802 0.0850 16.7799 0.0496 0.0226 0.0840 0.0003 -0.0036 1.5340 0.5671 2.7968 2.7968 1.9493 0.2723 0.0749 0.0850 16.1814 0.0482 0.0213 0.0787 0.0004 -0.0037 1.6114 0.5504 2.8339 2.8339 1.9490 0.2652 0.0700 0.0850 15.6373 0.0468 0.0201 0.0738 0.0005 -0.0038 1.6888 0.5338 2.8711 2.8711 1.9487 0.2580 0.0655 0.0850 15.1406 0.0454 0.0189 0.0693 0.0006 -0.0039 1.7662 0.5172 2.9083 2.9083 1.9484 0.2505 0.0614 0.0850 14.6853 0.0440 0.0177 0.0651 0.0007 -0.0039 1.8436 0.5006 2.9455 2.9455 1.9480 0.2430 0.0575 0.0850 14.2666 0.0425 0.0166 0.0613 0.0007 -0.0038 1.9210 0.4840 2.9827 2.9827 1.9477 0.2354 0.0540 0.0850 13.8803 0.0411 0.0155 0.0578 0.0007 -0.0037 1.9984 0.4673 3.0199 3.0199 1.9475 0.2276 0.0508 0.0850 13.5228 0.0397 0.0145 0.0545 0.0007 -0.0036 2.0759 0.4507 3.0570 3.0570 1.9473 0.2198 0.0478 0.0850 13.1909 0.0383 0.0135 0.0514 0.0007 -0.0034 2.1533 0.4341 3.0942 3.0942 1.9472 0.2120 0.0450 0.0850 12.8822 0.0369 0.0125 0.0485 0.0006 -0.0032 2.2307 0.4175 3.1314 3.1314 1.9472 0.2040 0.0423 0.0850 12.5941 0.0355 0.0115 0.0458 0.0005 -0.0030 2.3081 0.4009 3.1686 3.1686 1.9473 0.1961 0.0398 0.0850 12.3248 0.0341 0.0106 0.0432 0.0005 -0.0027 2.3855 0.3842 3.2058 3.2058 1.9477 0.1881 0.0374 0.0850 12.0725 0.0327 0.0098 0.0407 0.0004 -0.0026 2.4629 0.3676 3.2429 3.2429 1.9482 0.1800 0.0351 0.0850 11.8356 0.0312 0.0090 0.0383 0.0003 -0.0024 2.5403 0.3510 3.2801 3.2801 1.9491 0.1720 0.0328 0.0850 11.6128 0.0298 0.0082 0.0359 0.0003 -0.0024 2.6178 0.3344 3.3173 3.3173 1.9503 0.1641 0.0305 0.0850 11.4028 0.0284 0.0074 0.0335 0.0003 -0.0024 2.6952 0.3177 3.3545 3.3545 1.9518 0.1561 0.0282 0.0850 11.2046 0.0270 0.0067 0.0311 0.0004 -0.0026 2.7726 0.3011 3.3917 3.3917 1.9538 0.1482 0.0258 0.0850 11.0172 0.0256 0.0060 0.0286 0.0005 -0.0029 2.8468 0.2852 3.4273 3.4273 1.9550 0.1407 0.0234 0.0850 10.8471 0.0242 0.0054 0.0261 0.0007 -0.0033 2.8652 0.2813 3.4361 3.4361 1.9556 0.1388 0.0228 0.0850 10.8062 0.0239 0.0052 0.0255 0.0008 -0.0035 2.8803 0.2780 3.4434 3.4434 1.9558 0.1373 0.0223 0.0850 10.7729 0.0236 0.0051 0.0249 0.0008 -0.0036 2.8955 0.2747 3.4507 3.4507 1.9580 0.1358 0.0218 0.0850 10.7400 0.0234 0.0050 0.0244 0.0009 -0.0037 2.9106 0.2715 3.4580 3.4580 1.9587 0.1342 0.0213 0.0850 10.7074 0.0231 0.0049 0.0238 0.0009 -0.0039 2.9258 0.2682 3.4652 3.4652 1.9593 0.1327 0.0207 0.0850 10.6751 0.0228 0.0048 0.0233 0.0010 -0.0040 2.9409 0.2632 3.4725 3.4728 1.9580 0.1303 0.0200 0.0850 10.6440 0.0224 0.0046 0.0226 0.0011 -0.0042 2.9561 0.2536 3.4798 3.4811 1.9621 0.1257 0.0189 0.0850 10.6153 0.0216 0.0043 0.0214 0.0011 -0.0043 2.9712 0.2369 3.4871 3.4907 1.9652 0.1175 0.0172 0.0850 10.5910 0.0201 0.0037 0.0194 0.0012 -0.0045 2.9864 0.2057 3.4944 3.5039 1.9719 0.1023 0.0141 0.0850 10.5773 0.0175 0.0028 0.0161 0.0013 -0.0047 3.0000 0.1222 3.5009 3.5330 3.5330 0.0617 0.0064 0.0850 10.6159 0.0104 0.0000 0.0063 0.0000 0.0000 RADIUS: 3.00 PROPELLER RADIUS (IN) HUBRAD: 0.24 HUB RADIUS (IN) HUBTRA: 0.55 HUB TRANSITION (IN) BLADES: 2 NUMBER OF BLADES ----- INERTIA AND AREA DATA ----- TOTAL WEIGHT (LB) = 0.009592 TOTAL WEIGHT (Kg) = 0.004350 TOTAL VOLUME (IN**3) = 0.156270 TOTAL PROJECTED AREA (IN**2) = 2.9411 MOMENT OF INERTIA (SNAIL-IN**2) = 0.000035 MOMENT OF INERTIA (Kg-M**2) = 0.000004 STATIC MOMENT, ONE SIDE (IN-LB) = 0.004440 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 = 99.173 INNER LIMIT (NORMALIZED BY RADIUS) = 0.080 ----- NATURAL FREQUENCY DATA ----- LOWEST NATURAL BENDING FREQUENCY (IN TERMS OF RPM) = 18290.89 BASED ON MODULUS (MILLION) = 2.70 AND, MATERIAL DENSITY (S.G.) = 1.70 ----- AIRFOIL SECTIONS ----- AIRFOIL1: 1.67, APC16009R (Transition Start, Airfoil 1) AIRFOIL2: 2.67, APC16009R (Transition End, Airfoil 2) AIRFOILS ARE SCALED BASED ON THICKNESS RATIO IN TABLE ABOVE.