FX 84-W-127 (fx84w127-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-127 (fx84w127-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.7 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w127-il-1000000-n5.txt Download as CSV file: xf-fx84w127-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-127
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.9816 0.03208 0.02891 -0.0949 0.9405 0.0074
-14.250 -0.9957 0.02983 0.02643 -0.0928 0.9097 0.0074
-14.000 -1.0025 0.02835 0.02478 -0.0899 0.8923 0.0075
-13.750 -1.0009 0.02710 0.02338 -0.0875 0.8806 0.0076
-13.500 -0.9934 0.02578 0.02191 -0.0860 0.8706 0.0077
-13.250 -0.9802 0.02475 0.02077 -0.0849 0.8626 0.0079
-13.000 -0.9657 0.02374 0.01963 -0.0839 0.8550 0.0080
-12.750 -0.9488 0.02283 0.01861 -0.0831 0.8485 0.0082
-12.500 -0.9305 0.02199 0.01765 -0.0824 0.8416 0.0084
-12.250 -0.9116 0.02117 0.01670 -0.0817 0.8355 0.0085
-12.000 -0.8916 0.02037 0.01579 -0.0811 0.8293 0.0087
-11.750 -0.8709 0.01962 0.01492 -0.0805 0.8234 0.0089
-11.500 -0.8492 0.01891 0.01410 -0.0800 0.8179 0.0090
-11.250 -0.8269 0.01825 0.01332 -0.0796 0.8118 0.0092
-10.750 -0.7803 0.01708 0.01193 -0.0789 0.8006 0.0095
-10.500 -0.7577 0.01632 0.01107 -0.0785 0.7947 0.0099
-10.250 -0.7337 0.01576 0.01042 -0.0782 0.7894 0.0102
-10.000 -0.7087 0.01526 0.00987 -0.0780 0.7840 0.0105
-9.750 -0.6835 0.01482 0.00935 -0.0778 0.7783 0.0108
-9.500 -0.6580 0.01440 0.00885 -0.0776 0.7734 0.0112
-9.250 -0.6322 0.01399 0.00836 -0.0775 0.7682 0.0115
-9.000 -0.6062 0.01360 0.00790 -0.0774 0.7629 0.0119
-8.750 -0.5799 0.01325 0.00747 -0.0773 0.7580 0.0122
-8.500 -0.5537 0.01284 0.00700 -0.0772 0.7530 0.0126
-8.250 -0.5273 0.01247 0.00657 -0.0771 0.7480 0.0133
-8.000 -0.5006 0.01217 0.00623 -0.0770 0.7433 0.0139
-7.750 -0.4735 0.01187 0.00589 -0.0770 0.7384 0.0146
-7.500 -0.4463 0.01160 0.00555 -0.0770 0.7331 0.0151
-7.250 -0.4191 0.01135 0.00523 -0.0770 0.7286 0.0155
-7.000 -0.3920 0.01102 0.00487 -0.0770 0.7242 0.0165
-6.750 -0.3646 0.01076 0.00458 -0.0770 0.7192 0.0173
-6.500 -0.3371 0.01054 0.00432 -0.0770 0.7142 0.0183
-6.250 -0.3093 0.01034 0.00408 -0.0771 0.7095 0.0193
-6.000 -0.2816 0.01010 0.00381 -0.0771 0.7044 0.0206
-5.750 -0.2540 0.00990 0.00358 -0.0772 0.6992 0.0219
-5.500 -0.2259 0.00972 0.00336 -0.0773 0.6943 0.0233
-5.250 -0.1979 0.00954 0.00315 -0.0773 0.6890 0.0247
-5.000 -0.1701 0.00936 0.00296 -0.0774 0.6838 0.0269
-4.750 -0.1418 0.00921 0.00278 -0.0775 0.6790 0.0289
-4.500 -0.1137 0.00905 0.00261 -0.0776 0.6738 0.0311
-4.250 -0.0856 0.00891 0.00245 -0.0777 0.6688 0.0339
-4.000 -0.0572 0.00879 0.00231 -0.0779 0.6642 0.0365
-3.750 -0.0290 0.00864 0.00216 -0.0780 0.6589 0.0409
-3.500 -0.0007 0.00854 0.00204 -0.0781 0.6539 0.0444
-3.250 0.0276 0.00840 0.00192 -0.0783 0.6494 0.0508
-3.000 0.0561 0.00829 0.00181 -0.0784 0.6441 0.0566
-2.750 0.0844 0.00819 0.00172 -0.0785 0.6389 0.0643
-2.500 0.1128 0.00808 0.00163 -0.0787 0.6343 0.0746
-2.250 0.1412 0.00797 0.00155 -0.0789 0.6291 0.0857
-2.000 0.1695 0.00788 0.00148 -0.0790 0.6237 0.0999
-1.750 0.1979 0.00778 0.00141 -0.0792 0.6186 0.1166
-1.500 0.2263 0.00768 0.00136 -0.0794 0.6128 0.1376
-1.000 0.2828 0.00746 0.00127 -0.0798 0.6012 0.1950
-0.750 0.3110 0.00733 0.00124 -0.0800 0.5955 0.2338
-0.500 0.3390 0.00717 0.00121 -0.0802 0.5904 0.2864
-0.250 0.3671 0.00696 0.00120 -0.0804 0.5855 0.3545
0.000 0.3948 0.00672 0.00119 -0.0806 0.5800 0.4401
0.250 0.4224 0.00649 0.00119 -0.0808 0.5749 0.5300
0.500 0.4502 0.00630 0.00122 -0.0809 0.5692 0.6077
0.750 0.4779 0.00619 0.00126 -0.0810 0.5637 0.6686
1.000 0.5058 0.00613 0.00131 -0.0810 0.5588 0.7134
1.250 0.5337 0.00610 0.00136 -0.0810 0.5530 0.7507
1.500 0.5613 0.00612 0.00142 -0.0810 0.5465 0.7772
1.750 0.5892 0.00613 0.00148 -0.0810 0.5402 0.8000
2.000 0.6162 0.00615 0.00156 -0.0808 0.5332 0.8286
2.250 0.6429 0.00617 0.00164 -0.0805 0.5274 0.8574
2.500 0.6698 0.00621 0.00172 -0.0803 0.5209 0.8755
2.750 0.6969 0.00628 0.00179 -0.0802 0.5149 0.8866
3.000 0.7244 0.00634 0.00186 -0.0801 0.5087 0.8971
3.250 0.7508 0.00642 0.00194 -0.0798 0.5020 0.9076
3.500 0.7775 0.00649 0.00203 -0.0796 0.4940 0.9174
3.750 0.8035 0.00660 0.00212 -0.0793 0.4840 0.9275
4.000 0.8291 0.00669 0.00221 -0.0789 0.4740 0.9381
4.250 0.8549 0.00678 0.00231 -0.0785 0.4660 0.9496
4.500 0.8817 0.00689 0.00241 -0.0784 0.4569 0.9626
4.750 0.9118 0.00700 0.00252 -0.0790 0.4479 0.9757
5.000 0.9443 0.00717 0.00265 -0.0802 0.4362 0.9899
5.250 0.9726 0.00740 0.00281 -0.0806 0.4175 1.0000
5.500 0.9955 0.00783 0.00306 -0.0800 0.3820 1.0000
5.750 1.0179 0.00829 0.00334 -0.0794 0.3458 1.0000
6.000 1.0406 0.00872 0.00363 -0.0788 0.3158 1.0000
6.250 1.0615 0.00927 0.00399 -0.0779 0.2793 1.0000
6.500 1.0821 0.00980 0.00436 -0.0770 0.2473 1.0000
6.750 1.1010 0.01042 0.00480 -0.0758 0.2101 1.0000
7.000 1.1189 0.01107 0.00526 -0.0745 0.1770 1.0000
7.250 1.1355 0.01174 0.00576 -0.0730 0.1433 1.0000
7.500 1.1517 0.01239 0.00625 -0.0713 0.1152 1.0000
7.750 1.1666 0.01305 0.00678 -0.0695 0.0908 1.0000
8.000 1.1796 0.01366 0.00729 -0.0673 0.0723 1.0000
8.250 1.1914 0.01422 0.00779 -0.0649 0.0598 1.0000
8.500 1.2047 0.01475 0.00829 -0.0628 0.0513 1.0000
8.750 1.2180 0.01532 0.00883 -0.0608 0.0438 1.0000
9.000 1.2315 0.01592 0.00942 -0.0590 0.0381 1.0000
9.250 1.2451 0.01654 0.01003 -0.0573 0.0335 1.0000
9.500 1.2594 0.01716 0.01065 -0.0557 0.0303 1.0000
9.750 1.2724 0.01787 0.01136 -0.0541 0.0268 1.0000
10.000 1.2864 0.01856 0.01207 -0.0527 0.0246 1.0000
10.250 1.3000 0.01931 0.01283 -0.0513 0.0226 1.0000
10.500 1.3124 0.02015 0.01368 -0.0498 0.0207 1.0000
10.750 1.3260 0.02093 0.01450 -0.0485 0.0197 1.0000
11.000 1.3387 0.02180 0.01540 -0.0472 0.0184 1.0000
11.250 1.3503 0.02278 0.01639 -0.0459 0.0172 1.0000
11.500 1.3614 0.02381 0.01746 -0.0446 0.0160 1.0000
11.750 1.3738 0.02480 0.01849 -0.0435 0.0153 1.0000
12.000 1.3851 0.02587 0.01960 -0.0424 0.0145 1.0000
12.250 1.3952 0.02707 0.02083 -0.0413 0.0137 1.0000
12.500 1.4046 0.02836 0.02215 -0.0402 0.0130 1.0000
12.750 1.4141 0.02967 0.02350 -0.0391 0.0124 1.0000
13.000 1.4239 0.03098 0.02488 -0.0382 0.0120 1.0000
13.250 1.4331 0.03238 0.02633 -0.0373 0.0115 1.0000
13.500 1.4417 0.03386 0.02785 -0.0365 0.0109 1.0000
13.750 1.4490 0.03549 0.02952 -0.0357 0.0104 1.0000
14.000 1.4552 0.03728 0.03136 -0.0349 0.0099 1.0000
14.250 1.4618 0.03909 0.03323 -0.0343 0.0096 1.0000
14.500 1.4694 0.04085 0.03505 -0.0337 0.0094 1.0000
14.750 1.4761 0.04273 0.03701 -0.0332 0.0092 1.0000
15.000 1.4824 0.04471 0.03905 -0.0329 0.0088 1.0000
15.250 1.4876 0.04687 0.04127 -0.0325 0.0085 1.0000
15.500 1.4925 0.04909 0.04355 -0.0323 0.0083 1.0000
15.750 1.4970 0.05140 0.04592 -0.0321 0.0080 1.0000
16.000 1.5000 0.05395 0.04853 -0.0321 0.0077 1.0000
16.250 1.5026 0.05662 0.05127 -0.0321 0.0075 1.0000
16.500 1.5037 0.05953 0.05426 -0.0323 0.0074 1.0000
16.750 1.5068 0.06223 0.05703 -0.0325 0.0072 1.0000
17.000 1.5085 0.06519 0.06009 -0.0329 0.0071 1.0000
17.250 1.5109 0.06813 0.06310 -0.0333 0.0069 1.0000
17.500 1.5120 0.07128 0.06634 -0.0339 0.0068 1.0000
17.750 1.5141 0.07434 0.06947 -0.0345 0.0065 1.0000
18.000 1.5137 0.07782 0.07304 -0.0354 0.0064 1.0000
18.250 1.5124 0.08150 0.07681 -0.0363 0.0063 1.0000
18.500 1.5110 0.08524 0.08064 -0.0374 0.0062 1.0000
18.750 1.5095 0.08908 0.08456 -0.0386 0.0061 1.0000
19.000 1.5068 0.09314 0.08870 -0.0400 0.0059 1.0000
19.250 1.5035 0.09737 0.09302 -0.0415 0.0058 1.0000
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