FX 84-W-150 (fx84w150-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 84-W-150 (fx84w150-il) Reynolds number: 200,000 Max Cl/Cd: 77.41 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx84w150-il-200000-n5.txt Download as CSV file: xf-fx84w150-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 84-W-150
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4008 0.06216 0.05824 -0.1002 0.9068 0.0247
-11.500 -0.4949 0.04418 0.03968 -0.1147 0.8877 0.0237
-11.250 -0.5190 0.04035 0.03556 -0.1147 0.8763 0.0239
-11.000 -0.5378 0.03757 0.03248 -0.1124 0.8664 0.0241
-10.750 -0.5476 0.03525 0.02985 -0.1101 0.8578 0.0245
-10.500 -0.5498 0.03289 0.02709 -0.1081 0.8510 0.0251
-10.250 -0.5464 0.03063 0.02437 -0.1064 0.8447 0.0257
-10.000 -0.5328 0.02933 0.02296 -0.1054 0.8386 0.0262
-9.750 -0.5166 0.02836 0.02187 -0.1044 0.8337 0.0268
-9.500 -0.4992 0.02737 0.02074 -0.1036 0.8284 0.0275
-9.250 -0.4812 0.02633 0.01951 -0.1028 0.8228 0.0284
-9.000 -0.4626 0.02522 0.01813 -0.1019 0.8180 0.0297
-8.750 -0.4429 0.02412 0.01678 -0.1011 0.8135 0.0309
-8.500 -0.4213 0.02342 0.01606 -0.1007 0.8080 0.0319
-8.250 -0.3993 0.02270 0.01523 -0.1001 0.8033 0.0330
-8.000 -0.3768 0.02190 0.01425 -0.0995 0.7996 0.0343
-7.750 -0.3536 0.02114 0.01330 -0.0991 0.7943 0.0359
-7.500 -0.3306 0.02047 0.01261 -0.0986 0.7893 0.0374
-7.250 -0.3065 0.01998 0.01203 -0.0983 0.7852 0.0393
-7.000 -0.2821 0.01940 0.01132 -0.0979 0.7813 0.0413
-6.750 -0.2579 0.01880 0.01064 -0.0975 0.7761 0.0432
-6.500 -0.2334 0.01834 0.01015 -0.0972 0.7715 0.0455
-6.250 -0.2082 0.01790 0.00960 -0.0968 0.7678 0.0482
-6.000 -0.1832 0.01742 0.00905 -0.0965 0.7633 0.0508
-5.750 -0.1583 0.01701 0.00864 -0.0963 0.7585 0.0539
-5.500 -0.1326 0.01664 0.00819 -0.0960 0.7542 0.0574
-5.250 -0.1071 0.01621 0.00770 -0.0957 0.7507 0.0611
-5.000 -0.0816 0.01590 0.00739 -0.0955 0.7456 0.0657
-4.750 -0.0558 0.01557 0.00702 -0.0953 0.7410 0.0707
-4.500 -0.0298 0.01525 0.00667 -0.0951 0.7370 0.0769
-4.250 -0.0035 0.01496 0.00634 -0.0949 0.7331 0.0841
-4.000 0.0226 0.01472 0.00609 -0.0948 0.7279 0.0928
-3.750 0.0488 0.01444 0.00584 -0.0946 0.7234 0.1037
-3.500 0.0755 0.01418 0.00557 -0.0945 0.7195 0.1173
-3.250 0.1017 0.01396 0.00538 -0.0944 0.7148 0.1344
-3.000 0.1280 0.01373 0.00521 -0.0943 0.7098 0.1558
-2.750 0.1545 0.01348 0.00503 -0.0942 0.7056 0.1848
-2.500 0.1812 0.01320 0.00483 -0.0942 0.7020 0.2229
-2.250 0.2065 0.01291 0.00475 -0.0941 0.6968 0.2751
-2.000 0.2316 0.01252 0.00464 -0.0939 0.6921 0.3535
-1.750 0.2562 0.01205 0.00454 -0.0935 0.6882 0.4624
-1.500 0.2800 0.01171 0.00458 -0.0928 0.6840 0.5722
-1.250 0.3041 0.01157 0.00469 -0.0919 0.6789 0.6484
-1.000 0.3293 0.01153 0.00474 -0.0911 0.6745 0.7001
-0.750 0.3554 0.01152 0.00474 -0.0905 0.6709 0.7368
-0.500 0.3805 0.01157 0.00484 -0.0898 0.6659 0.7653
-0.250 0.4056 0.01162 0.00490 -0.0890 0.6610 0.7894
0.000 0.4313 0.01165 0.00491 -0.0884 0.6568 0.8109
0.250 0.4565 0.01171 0.00494 -0.0877 0.6526 0.8306
0.500 0.4794 0.01179 0.00506 -0.0864 0.6474 0.8514
0.750 0.5015 0.01184 0.00512 -0.0848 0.6428 0.8750
1.000 0.5253 0.01187 0.00510 -0.0836 0.6389 0.8942
1.250 0.5493 0.01194 0.00519 -0.0828 0.6334 0.9063
1.500 0.5754 0.01198 0.00521 -0.0824 0.6283 0.9173
1.750 0.6028 0.01201 0.00517 -0.0823 0.6240 0.9281
2.000 0.6317 0.01207 0.00524 -0.0826 0.6189 0.9374
2.250 0.6616 0.01214 0.00530 -0.0831 0.6136 0.9471
2.500 0.6936 0.01219 0.00531 -0.0841 0.6092 0.9565
2.750 0.7280 0.01228 0.00538 -0.0857 0.6043 0.9643
3.000 0.7617 0.01238 0.00550 -0.0872 0.5986 0.9732
3.250 0.7972 0.01246 0.00556 -0.0890 0.5940 0.9815
3.500 0.8333 0.01256 0.00564 -0.0910 0.5891 0.9897
3.750 0.8662 0.01269 0.00581 -0.0925 0.5830 1.0000
4.000 0.8865 0.01281 0.00589 -0.0914 0.5781 1.0000
4.250 0.9086 0.01295 0.00602 -0.0906 0.5728 1.0000
4.500 0.9310 0.01311 0.00621 -0.0898 0.5666 1.0000
4.750 0.9560 0.01325 0.00631 -0.0895 0.5613 1.0000
5.000 0.9795 0.01344 0.00653 -0.0890 0.5552 1.0000
5.250 1.0036 0.01361 0.00673 -0.0886 0.5490 1.0000
5.500 1.0294 0.01378 0.00686 -0.0884 0.5440 1.0000
5.750 1.0521 0.01400 0.00716 -0.0878 0.5372 1.0000
6.000 1.0766 0.01419 0.00736 -0.0874 0.5312 1.0000
6.250 1.0997 0.01441 0.00760 -0.0868 0.5240 1.0000
6.500 1.1223 0.01461 0.00782 -0.0861 0.5158 1.0000
6.750 1.1445 0.01485 0.00810 -0.0854 0.5080 1.0000
7.000 1.1665 0.01509 0.00838 -0.0846 0.5005 1.0000
7.250 1.1882 0.01535 0.00868 -0.0838 0.4932 1.0000
7.500 1.2086 0.01562 0.00899 -0.0828 0.4850 1.0000
7.750 1.2280 0.01592 0.00934 -0.0816 0.4763 1.0000
8.000 1.2431 0.01623 0.00964 -0.0797 0.4630 1.0000
8.250 1.2519 0.01661 0.00999 -0.0766 0.4465 1.0000
8.500 1.2599 0.01710 0.01045 -0.0736 0.4292 1.0000
8.750 1.2690 0.01767 0.01100 -0.0710 0.4129 1.0000
9.000 1.2777 0.01833 0.01164 -0.0685 0.3960 1.0000
9.250 1.2851 0.01910 0.01237 -0.0660 0.3780 1.0000
9.500 1.2908 0.02001 0.01323 -0.0634 0.3591 1.0000
9.750 1.2951 0.02108 0.01423 -0.0608 0.3385 1.0000
10.000 1.2988 0.02226 0.01537 -0.0584 0.3171 1.0000
10.250 1.2994 0.02370 0.01672 -0.0558 0.2941 1.0000
10.500 1.2992 0.02530 0.01823 -0.0533 0.2705 1.0000
10.750 1.2972 0.02712 0.01995 -0.0509 0.2467 1.0000
11.000 1.2945 0.02911 0.02184 -0.0486 0.2227 1.0000
11.250 1.2913 0.03125 0.02387 -0.0466 0.1995 1.0000
11.500 1.2872 0.03357 0.02610 -0.0447 0.1772 1.0000
11.750 1.2849 0.03588 0.02833 -0.0431 0.1553 1.0000
12.000 1.2812 0.03842 0.03078 -0.0416 0.1349 1.0000
12.250 1.2791 0.04094 0.03322 -0.0404 0.1163 1.0000
12.500 1.2772 0.04353 0.03576 -0.0393 0.1006 1.0000
12.750 1.2764 0.04612 0.03831 -0.0385 0.0880 1.0000
13.000 1.2771 0.04867 0.04085 -0.0378 0.0783 1.0000
13.250 1.2777 0.05128 0.04347 -0.0372 0.0704 1.0000
13.500 1.2790 0.05391 0.04612 -0.0368 0.0638 1.0000
13.750 1.2812 0.05650 0.04876 -0.0364 0.0583 1.0000
14.000 1.2820 0.05930 0.05159 -0.0362 0.0540 1.0000
14.250 1.2842 0.06202 0.05438 -0.0361 0.0504 1.0000
14.500 1.2861 0.06481 0.05724 -0.0360 0.0473 1.0000
15.000 1.2883 0.07081 0.06337 -0.0362 0.0423 1.0000
15.250 1.2901 0.07379 0.06644 -0.0365 0.0401 1.0000
15.500 1.2899 0.07708 0.06978 -0.0368 0.0383 1.0000
15.750 1.2896 0.08046 0.07323 -0.0373 0.0368 1.0000
16.000 1.2923 0.08347 0.07636 -0.0377 0.0352 1.0000
16.250 1.2940 0.08664 0.07963 -0.0383 0.0338 1.0000
16.500 1.2944 0.09005 0.08311 -0.0390 0.0325 1.0000
16.750 1.2929 0.09376 0.08686 -0.0399 0.0314 1.0000
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