BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BELL/WORTMANN FX 69-H-083 AIRFOIL (fx69h083-il) Reynolds number: 50,000 Max Cl/Cd: 37.01 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx69h083-il-50000-n5.txt Download as CSV file: xf-fx69h083-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BELL/WORTMANN FX 69-H-083 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4932 0.11458 0.10807 -0.0032 1.0000 0.0952
-9.000 -0.4975 0.11184 0.10543 -0.0072 1.0000 0.0990
-8.750 -0.5072 0.10941 0.10312 -0.0134 1.0000 0.1002
-8.500 -0.4923 0.10384 0.09756 -0.0113 1.0000 0.1022
-8.250 -0.4832 0.09978 0.09352 -0.0113 1.0000 0.1051
-8.000 -0.4802 0.09613 0.08994 -0.0133 1.0000 0.1082
-7.750 -0.4941 0.09358 0.08746 -0.0230 1.0000 0.1140
-7.500 -0.3856 0.07289 0.06710 -0.0284 1.0000 0.0666
-7.250 -0.3919 0.06774 0.06195 -0.0317 1.0000 0.0554
-7.000 -0.4586 0.07589 0.06960 -0.0310 1.0000 0.0567
-6.750 -0.4505 0.07158 0.06529 -0.0316 1.0000 0.0526
-6.500 -0.4412 0.06598 0.05923 -0.0364 1.0000 0.0451
-6.250 -0.4318 0.06197 0.05527 -0.0359 1.0000 0.0440
-6.000 -0.4229 0.05822 0.05141 -0.0357 1.0000 0.0432
-5.750 -0.4140 0.05464 0.04763 -0.0353 1.0000 0.0432
-5.500 -0.4053 0.05133 0.04402 -0.0342 1.0000 0.0439
-5.250 -0.3959 0.04827 0.04055 -0.0328 1.0000 0.0447
-5.000 -0.3847 0.04558 0.03740 -0.0310 1.0000 0.0453
-4.500 -0.3589 0.03980 0.03093 -0.0276 1.0000 0.0453
-4.250 -0.3431 0.03714 0.02785 -0.0260 1.0000 0.0453
-4.000 -0.3259 0.03437 0.02466 -0.0247 1.0000 0.0458
-3.750 -0.3070 0.03199 0.02196 -0.0236 1.0000 0.0470
-3.500 -0.2881 0.03046 0.02026 -0.0227 1.0000 0.0518
-3.250 -0.2659 0.02891 0.01823 -0.0216 1.0000 0.0564
-3.000 -0.2298 0.02701 0.01580 -0.0227 0.9952 0.0584
-2.750 -0.1924 0.02516 0.01379 -0.0243 0.9895 0.0618
-2.500 -0.1534 0.02391 0.01226 -0.0262 0.9835 0.0676
-2.250 -0.1148 0.02293 0.01102 -0.0284 0.9771 0.0819
-2.000 -0.0785 0.02193 0.00998 -0.0304 0.9694 0.1081
-1.750 -0.0129 0.01791 0.00911 -0.0363 0.9745 1.0000
-1.500 0.0280 0.01806 0.00868 -0.0393 0.9653 1.0000
-1.250 0.0689 0.01821 0.00835 -0.0423 0.9559 1.0000
-1.000 0.1074 0.01836 0.00817 -0.0449 0.9455 1.0000
-0.750 0.1443 0.01853 0.00806 -0.0471 0.9348 1.0000
-0.500 0.1808 0.01870 0.00797 -0.0491 0.9243 1.0000
-0.250 0.2170 0.01886 0.00795 -0.0510 0.9140 1.0000
0.000 0.2479 0.01905 0.00800 -0.0518 0.9019 1.0000
0.250 0.2770 0.01925 0.00808 -0.0522 0.8893 1.0000
0.500 0.3053 0.01944 0.00817 -0.0523 0.8766 1.0000
0.750 0.3326 0.01962 0.00828 -0.0522 0.8636 1.0000
1.000 0.3590 0.01980 0.00841 -0.0519 0.8506 1.0000
1.250 0.3847 0.01998 0.00857 -0.0514 0.8374 1.0000
1.500 0.4099 0.02015 0.00872 -0.0507 0.8244 1.0000
1.750 0.4348 0.02033 0.00889 -0.0500 0.8115 1.0000
2.000 0.4595 0.02051 0.00908 -0.0492 0.7988 1.0000
2.250 0.4844 0.02068 0.00932 -0.0484 0.7861 1.0000
2.500 0.5093 0.02085 0.00954 -0.0476 0.7734 1.0000
2.750 0.5339 0.02101 0.00976 -0.0468 0.7605 1.0000
3.000 0.5584 0.02118 0.01001 -0.0458 0.7473 1.0000
3.250 0.5825 0.02136 0.01028 -0.0448 0.7335 1.0000
3.500 0.6062 0.02154 0.01064 -0.0438 0.7187 1.0000
3.750 0.6297 0.02173 0.01095 -0.0427 0.7032 1.0000
4.000 0.6533 0.02189 0.01126 -0.0415 0.6870 1.0000
4.250 0.6772 0.02204 0.01155 -0.0403 0.6707 1.0000
4.500 0.7013 0.02218 0.01193 -0.0391 0.6544 1.0000
4.750 0.7257 0.02232 0.01225 -0.0379 0.6383 1.0000
5.000 0.7486 0.02252 0.01265 -0.0366 0.6184 1.0000
5.250 0.7722 0.02258 0.01288 -0.0350 0.5972 1.0000
5.500 0.7944 0.02271 0.01320 -0.0333 0.5719 1.0000
5.750 0.8164 0.02288 0.01357 -0.0316 0.5452 1.0000
6.000 0.8381 0.02310 0.01413 -0.0300 0.5168 1.0000
6.250 0.8587 0.02333 0.01455 -0.0280 0.4823 1.0000
6.500 0.8741 0.02362 0.01483 -0.0252 0.4201 1.0000
6.750 0.8790 0.02477 0.01523 -0.0215 0.2822 1.0000
7.000 0.8766 0.02781 0.01693 -0.0187 0.1345 1.0000
7.250 0.8796 0.03084 0.01942 -0.0164 0.0797 1.0000
7.500 0.8883 0.03306 0.02162 -0.0144 0.0574 1.0000
7.750 0.8979 0.03513 0.02380 -0.0123 0.0498 1.0000
8.000 0.9092 0.03712 0.02593 -0.0103 0.0446 1.0000
8.250 0.9230 0.03923 0.02815 -0.0085 0.0401 1.0000
8.500 0.9410 0.04118 0.03039 -0.0070 0.0349 1.0000
8.750 0.9600 0.04353 0.03290 -0.0058 0.0321 1.0000
9.000 0.9823 0.04686 0.03654 -0.0048 0.0304 1.0000
9.250 1.0006 0.05038 0.04043 -0.0037 0.0296 1.0000
9.500 1.0118 0.05387 0.04439 -0.0022 0.0292 1.0000
9.750 1.0166 0.05746 0.04843 -0.0006 0.0288 1.0000
10.000 1.0155 0.06107 0.05246 0.0012 0.0284 1.0000
10.250 1.0082 0.06459 0.05632 0.0030 0.0281 1.0000
10.500 0.9969 0.06826 0.06029 0.0044 0.0279 1.0000
10.750 0.9833 0.07230 0.06458 0.0049 0.0278 1.0000
11.000 0.9681 0.07676 0.06928 0.0044 0.0279 1.0000
11.250 0.9516 0.08175 0.07446 0.0030 0.0280 1.0000
11.500 0.9347 0.08731 0.08018 0.0006 0.0282 1.0000
11.750 0.9179 0.09346 0.08645 -0.0026 0.0286 1.0000
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Polar data table (+)
Polar graphs
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