FX 84-W-127 (fx84w127-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 84-W-127 (fx84w127-il) Reynolds number: 1,000,000 Max Cl/Cd: 142.54 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx84w127-il-1000000.txt Download as CSV file: xf-fx84w127-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.2946 0.13512 0.13337 -0.0293 0.8977 0.0155
-13.500 -0.8014 0.04487 0.04261 -0.0820 1.0000 0.0105
-13.250 -0.8355 0.03642 0.03390 -0.0896 1.0000 0.0105
-13.000 -0.8286 0.03286 0.03017 -0.0945 0.9672 0.0106
-12.750 -0.8434 0.03004 0.02703 -0.0932 0.9276 0.0106
-12.500 -0.8427 0.02908 0.02594 -0.0905 0.9112 0.0108
-12.000 -0.8276 0.02650 0.02303 -0.0874 0.8894 0.0111
-11.750 -0.8152 0.02535 0.02171 -0.0862 0.8812 0.0114
-11.500 -0.8003 0.02424 0.02045 -0.0852 0.8732 0.0116
-11.250 -0.7842 0.02317 0.01920 -0.0843 0.8662 0.0118
-11.000 -0.7660 0.02218 0.01806 -0.0836 0.8591 0.0120
-10.500 -0.7305 0.01976 0.01526 -0.0819 0.8462 0.0125
-10.250 -0.7139 0.01827 0.01357 -0.0810 0.8398 0.0129
-10.000 -0.6912 0.01759 0.01280 -0.0806 0.8341 0.0133
-9.750 -0.6672 0.01704 0.01218 -0.0803 0.8282 0.0136
-9.500 -0.6431 0.01651 0.01155 -0.0800 0.8227 0.0140
-9.250 -0.6185 0.01593 0.01088 -0.0797 0.8174 0.0145
-9.000 -0.5935 0.01540 0.01025 -0.0795 0.8118 0.0149
-8.750 -0.5681 0.01499 0.00972 -0.0793 0.8066 0.0153
-8.500 -0.5430 0.01437 0.00901 -0.0790 0.8015 0.0157
-8.250 -0.5195 0.01351 0.00806 -0.0787 0.7962 0.0166
-8.000 -0.4933 0.01317 0.00766 -0.0785 0.7911 0.0173
-7.750 -0.4664 0.01286 0.00731 -0.0785 0.7861 0.0181
-7.500 -0.4395 0.01256 0.00694 -0.0784 0.7809 0.0188
-7.250 -0.4124 0.01231 0.00661 -0.0784 0.7761 0.0194
-7.000 -0.3872 0.01160 0.00583 -0.0781 0.7714 0.0206
-6.750 -0.3600 0.01128 0.00549 -0.0781 0.7662 0.0215
-6.500 -0.3327 0.01104 0.00518 -0.0781 0.7612 0.0227
-6.250 -0.3049 0.01082 0.00493 -0.0781 0.7564 0.0237
-6.000 -0.2781 0.01039 0.00445 -0.0781 0.7513 0.0254
-5.750 -0.2506 0.01015 0.00418 -0.0781 0.7461 0.0271
-5.500 -0.2227 0.00996 0.00395 -0.0781 0.7412 0.0287
-5.250 -0.1950 0.00969 0.00363 -0.0782 0.7359 0.0305
-5.000 -0.1674 0.00944 0.00337 -0.0782 0.7309 0.0333
-4.750 -0.1392 0.00930 0.00320 -0.0783 0.7260 0.0356
-4.500 -0.1114 0.00903 0.00291 -0.0783 0.7209 0.0391
-4.250 -0.0833 0.00887 0.00274 -0.0784 0.7160 0.0426
-4.000 -0.0552 0.00871 0.00254 -0.0785 0.7112 0.0466
-3.750 -0.0269 0.00853 0.00238 -0.0786 0.7061 0.0522
-3.500 0.0012 0.00837 0.00221 -0.0787 0.7011 0.0591
-3.250 0.0295 0.00825 0.00208 -0.0788 0.6964 0.0667
-3.000 0.0579 0.00808 0.00196 -0.0790 0.6913 0.0777
-2.750 0.0861 0.00793 0.00184 -0.0791 0.6862 0.0930
-2.500 0.1143 0.00778 0.00174 -0.0793 0.6814 0.1130
-2.000 0.1708 0.00746 0.00157 -0.0796 0.6711 0.1691
-1.750 0.1988 0.00728 0.00150 -0.0798 0.6660 0.2104
-1.500 0.2269 0.00704 0.00144 -0.0800 0.6605 0.2670
-1.250 0.2545 0.00677 0.00138 -0.0802 0.6549 0.3438
-1.000 0.2817 0.00639 0.00134 -0.0804 0.6497 0.4593
-0.750 0.3089 0.00602 0.00132 -0.0805 0.6443 0.5795
-0.500 0.3361 0.00581 0.00133 -0.0804 0.6390 0.6673
-0.250 0.3639 0.00570 0.00136 -0.0804 0.6342 0.7233
0.000 0.3917 0.00564 0.00140 -0.0803 0.6288 0.7617
0.250 0.4195 0.00564 0.00143 -0.0803 0.6234 0.7899
0.500 0.4475 0.00563 0.00146 -0.0802 0.6182 0.8128
0.750 0.4754 0.00565 0.00150 -0.0802 0.6128 0.8325
1.000 0.5030 0.00569 0.00154 -0.0801 0.6075 0.8498
1.500 0.5579 0.00573 0.00163 -0.0798 0.5960 0.8807
1.750 0.5847 0.00578 0.00168 -0.0795 0.5901 0.8940
2.000 0.6109 0.00580 0.00173 -0.0790 0.5839 0.9106
2.250 0.6349 0.00584 0.00179 -0.0781 0.5780 0.9297
2.500 0.6588 0.00586 0.00184 -0.0771 0.5724 0.9456
2.750 0.6838 0.00590 0.00188 -0.0764 0.5662 0.9585
3.000 0.7106 0.00596 0.00192 -0.0761 0.5603 0.9709
3.250 0.7433 0.00600 0.00197 -0.0772 0.5540 0.9801
3.750 0.8132 0.00616 0.00209 -0.0806 0.5382 0.9941
4.000 0.8490 0.00628 0.00217 -0.0825 0.5303 1.0000
4.250 0.8741 0.00635 0.00225 -0.0821 0.5234 1.0000
4.500 0.9000 0.00650 0.00235 -0.0819 0.5160 1.0000
4.750 0.9275 0.00658 0.00245 -0.0820 0.5085 1.0000
5.000 0.9541 0.00673 0.00257 -0.0819 0.4996 1.0000
5.250 0.9807 0.00688 0.00269 -0.0819 0.4867 1.0000
5.500 1.0066 0.00708 0.00282 -0.0817 0.4672 1.0000
5.750 1.0323 0.00729 0.00298 -0.0815 0.4489 1.0000
6.000 1.0579 0.00752 0.00315 -0.0813 0.4329 1.0000
6.250 1.0831 0.00777 0.00334 -0.0811 0.4158 1.0000
6.500 1.1076 0.00806 0.00356 -0.0807 0.3966 1.0000
6.750 1.1315 0.00839 0.00381 -0.0802 0.3733 1.0000
7.000 1.1538 0.00880 0.00411 -0.0796 0.3468 1.0000
7.250 1.1749 0.00929 0.00446 -0.0787 0.3156 1.0000
7.500 1.1930 0.00994 0.00490 -0.0774 0.2768 1.0000
7.750 1.2084 0.01072 0.00545 -0.0757 0.2326 1.0000
8.000 1.2215 0.01156 0.00605 -0.0736 0.1900 1.0000
8.250 1.2328 0.01243 0.00669 -0.0713 0.1498 1.0000
8.500 1.2411 0.01327 0.00734 -0.0684 0.1161 1.0000
8.750 1.2458 0.01411 0.00803 -0.0648 0.0897 1.0000
9.000 1.2525 0.01494 0.00876 -0.0618 0.0709 1.0000
9.250 1.2620 0.01571 0.00947 -0.0594 0.0575 1.0000
9.500 1.2722 0.01651 0.01021 -0.0573 0.0477 1.0000
9.750 1.2824 0.01734 0.01102 -0.0552 0.0402 1.0000
10.000 1.2949 0.01809 0.01177 -0.0535 0.0358 1.0000
10.250 1.3054 0.01900 0.01268 -0.0517 0.0316 1.0000
10.500 1.3183 0.01980 0.01350 -0.0503 0.0291 1.0000
10.750 1.3278 0.02084 0.01455 -0.0486 0.0264 1.0000
11.000 1.3397 0.02177 0.01552 -0.0472 0.0247 1.0000
11.250 1.3515 0.02274 0.01652 -0.0459 0.0231 1.0000
11.500 1.3605 0.02393 0.01773 -0.0444 0.0215 1.0000
11.750 1.3688 0.02521 0.01905 -0.0429 0.0201 1.0000
12.000 1.3803 0.02628 0.02018 -0.0418 0.0193 1.0000
12.250 1.3905 0.02748 0.02142 -0.0407 0.0183 1.0000
12.500 1.3985 0.02889 0.02286 -0.0395 0.0174 1.0000
12.750 1.4021 0.03070 0.02472 -0.0381 0.0164 1.0000
13.000 1.4092 0.03227 0.02636 -0.0371 0.0158 1.0000
13.250 1.4188 0.03368 0.02783 -0.0363 0.0153 1.0000
13.500 1.4277 0.03516 0.02936 -0.0355 0.0146 1.0000
13.750 1.4349 0.03686 0.03111 -0.0348 0.0141 1.0000
14.000 1.4402 0.03878 0.03307 -0.0341 0.0135 1.0000
14.250 1.4408 0.04124 0.03560 -0.0333 0.0130 1.0000
14.500 1.4392 0.04400 0.03845 -0.0326 0.0125 1.0000
14.750 1.4467 0.04590 0.04042 -0.0323 0.0123 1.0000
15.000 1.4531 0.04797 0.04256 -0.0320 0.0120 1.0000
15.250 1.4571 0.05036 0.04503 -0.0318 0.0116 1.0000
15.500 1.4611 0.05279 0.04754 -0.0317 0.0113 1.0000
15.750 1.4663 0.05512 0.04993 -0.0317 0.0110 1.0000
16.000 1.4686 0.05789 0.05276 -0.0318 0.0107 1.0000
16.250 1.4707 0.06072 0.05565 -0.0320 0.0105 1.0000
16.500 1.4687 0.06414 0.05915 -0.0324 0.0103 1.0000
16.750 1.4603 0.06851 0.06361 -0.0330 0.0099 1.0000
17.000 1.4532 0.07284 0.06805 -0.0338 0.0097 1.0000
17.250 1.4574 0.07569 0.07099 -0.0344 0.0096 1.0000
17.500 1.4584 0.07902 0.07442 -0.0353 0.0094 1.0000
17.750 1.4610 0.08220 0.07768 -0.0361 0.0091 1.0000
18.000 1.4589 0.08613 0.08171 -0.0372 0.0090 1.0000
18.250 1.4573 0.09006 0.08573 -0.0385 0.0088 1.0000
18.500 1.4550 0.09411 0.08987 -0.0398 0.0087 1.0000
18.750 1.4531 0.09820 0.09405 -0.0413 0.0086 1.0000
19.000 1.4507 0.10242 0.09836 -0.0429 0.0084 1.0000
19.250 1.4474 0.10686 0.10288 -0.0447 0.0082 1.0000
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