BELL/WORTMANN FX 69-H-098 AIRFOIL (fx69h098-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: BELL/WORTMANN FX 69-H-098 AIRFOIL (fx69h098-il) Reynolds number: 50,000 Max Cl/Cd: 31.23 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx69h098-il-50000-n5.txt Download as CSV file: xf-fx69h098-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BELL/WORTMANN FX 69-H-098 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 -0.5214 0.09871 0.09169 -0.0155 1.0000 0.0587
-9.000 -0.5240 0.09369 0.08674 -0.0184 1.0000 0.0565
-8.500 -0.5607 0.07947 0.07244 -0.0312 1.0000 0.0505
-8.250 -0.5590 0.07550 0.06846 -0.0313 1.0000 0.0499
-8.000 -0.5595 0.07146 0.06436 -0.0315 1.0000 0.0494
-7.750 -0.5603 0.06738 0.06018 -0.0315 1.0000 0.0490
-7.500 -0.5606 0.06334 0.05596 -0.0312 1.0000 0.0488
-7.250 -0.5594 0.05942 0.05180 -0.0305 1.0000 0.0489
-7.000 -0.5563 0.05569 0.04774 -0.0294 1.0000 0.0493
-6.750 -0.5505 0.05223 0.04392 -0.0279 1.0000 0.0497
-6.500 -0.5421 0.04902 0.04032 -0.0262 1.0000 0.0501
-6.250 -0.5313 0.04595 0.03689 -0.0244 1.0000 0.0502
-6.000 -0.5185 0.04303 0.03357 -0.0226 1.0000 0.0501
-5.750 -0.5038 0.04031 0.03046 -0.0208 1.0000 0.0502
-5.500 -0.4871 0.03781 0.02756 -0.0191 1.0000 0.0504
-5.250 -0.4687 0.03555 0.02489 -0.0175 1.0000 0.0507
-5.000 -0.4491 0.03326 0.02236 -0.0161 1.0000 0.0514
-4.750 -0.4285 0.03130 0.02021 -0.0149 1.0000 0.0526
-4.500 -0.4075 0.02978 0.01855 -0.0137 1.0000 0.0552
-4.250 -0.3855 0.02845 0.01704 -0.0125 1.0000 0.0589
-4.000 -0.3622 0.02716 0.01552 -0.0113 1.0000 0.0621
-3.750 -0.3386 0.02590 0.01411 -0.0101 1.0000 0.0647
-3.500 -0.3162 0.02472 0.01292 -0.0090 1.0000 0.0688
-3.250 -0.2935 0.02381 0.01184 -0.0079 1.0000 0.0761
-3.000 -0.2707 0.02289 0.01090 -0.0071 1.0000 0.0888
-2.750 -0.2490 0.02187 0.00996 -0.0061 1.0000 0.1118
-2.250 -0.0855 0.01799 0.00920 -0.0231 1.0000 1.0000
-2.000 -0.0761 0.01791 0.00890 -0.0204 1.0000 1.0000
-1.750 -0.0661 0.01788 0.00868 -0.0178 1.0000 1.0000
-1.500 -0.0554 0.01792 0.00850 -0.0153 1.0000 1.0000
-1.250 -0.0443 0.01800 0.00841 -0.0128 1.0000 1.0000
-1.000 -0.0330 0.01813 0.00838 -0.0105 1.0000 1.0000
-0.750 0.0039 0.01831 0.00835 -0.0131 0.9904 1.0000
-0.500 0.0557 0.01846 0.00829 -0.0184 0.9746 1.0000
-0.250 0.1035 0.01853 0.00821 -0.0227 0.9567 1.0000
0.000 0.1513 0.01854 0.00811 -0.0269 0.9381 1.0000
0.250 0.1972 0.01849 0.00798 -0.0305 0.9184 1.0000
0.500 0.2348 0.01841 0.00784 -0.0322 0.8938 1.0000
0.750 0.2709 0.01831 0.00769 -0.0335 0.8676 1.0000
1.000 0.3059 0.01819 0.00752 -0.0343 0.8391 1.0000
1.250 0.3392 0.01809 0.00736 -0.0347 0.8080 1.0000
1.500 0.3707 0.01801 0.00718 -0.0346 0.7743 1.0000
1.750 0.3981 0.01803 0.00708 -0.0337 0.7368 1.0000
2.000 0.4239 0.01812 0.00702 -0.0325 0.6981 1.0000
2.250 0.4478 0.01830 0.00702 -0.0311 0.6584 1.0000
2.500 0.4710 0.01855 0.00708 -0.0297 0.6210 1.0000
2.750 0.4937 0.01887 0.00721 -0.0283 0.5869 1.0000
3.000 0.5163 0.01925 0.00743 -0.0270 0.5567 1.0000
3.250 0.5389 0.01966 0.00770 -0.0258 0.5300 1.0000
3.500 0.5620 0.02011 0.00801 -0.0248 0.5069 1.0000
3.750 0.5855 0.02057 0.00844 -0.0240 0.4851 1.0000
4.000 0.6095 0.02105 0.00885 -0.0232 0.4665 1.0000
4.250 0.6336 0.02155 0.00930 -0.0225 0.4496 1.0000
4.500 0.6578 0.02206 0.00979 -0.0219 0.4339 1.0000
4.750 0.6822 0.02260 0.01037 -0.0212 0.4194 1.0000
5.000 0.7064 0.02317 0.01098 -0.0206 0.4057 1.0000
5.250 0.7304 0.02376 0.01165 -0.0200 0.3926 1.0000
5.500 0.7544 0.02439 0.01237 -0.0194 0.3804 1.0000
5.750 0.7783 0.02505 0.01316 -0.0187 0.3690 1.0000
6.000 0.8024 0.02573 0.01390 -0.0181 0.3586 1.0000
6.250 0.8259 0.02645 0.01477 -0.0175 0.3481 1.0000
6.500 0.8488 0.02723 0.01573 -0.0167 0.3375 1.0000
6.750 0.8720 0.02800 0.01668 -0.0160 0.3280 1.0000
7.000 0.8948 0.02880 0.01765 -0.0153 0.3182 1.0000
7.250 0.9162 0.02969 0.01879 -0.0144 0.3077 1.0000
7.500 0.9378 0.03051 0.01981 -0.0135 0.2973 1.0000
7.750 0.9586 0.03118 0.02062 -0.0124 0.2852 1.0000
8.000 0.9772 0.03175 0.02142 -0.0110 0.2706 1.0000
8.250 0.9940 0.03227 0.02219 -0.0094 0.2543 1.0000
8.500 1.0097 0.03275 0.02290 -0.0077 0.2369 1.0000
8.750 1.0238 0.03305 0.02332 -0.0058 0.2174 1.0000
9.000 1.0349 0.03357 0.02404 -0.0037 0.1944 1.0000
9.250 1.0445 0.03430 0.02492 -0.0015 0.1696 1.0000
9.500 1.0518 0.03547 0.02617 0.0007 0.1421 1.0000
9.750 1.0557 0.03711 0.02773 0.0030 0.1171 1.0000
10.000 1.0570 0.03922 0.02979 0.0053 0.0992 1.0000
10.250 1.0554 0.04153 0.03206 0.0077 0.0875 1.0000
10.500 1.0501 0.04393 0.03442 0.0103 0.0801 1.0000
10.750 1.0462 0.04655 0.03716 0.0123 0.0737 1.0000
11.000 1.0399 0.04942 0.04000 0.0137 0.0697 1.0000
11.250 1.0363 0.05254 0.04337 0.0147 0.0653 1.0000
11.500 1.0310 0.05590 0.04687 0.0150 0.0616 1.0000
11.750 1.0254 0.05940 0.05039 0.0148 0.0586 1.0000
12.000 1.0208 0.06317 0.05428 0.0146 0.0563 1.0000
12.250 1.0151 0.06745 0.05885 0.0137 0.0544 1.0000
12.500 1.0075 0.07215 0.06379 0.0124 0.0527 1.0000
12.750 0.9986 0.07722 0.06907 0.0105 0.0512 1.0000
13.000 0.9888 0.08257 0.07459 0.0082 0.0499 1.0000
13.250 0.9788 0.08808 0.08024 0.0058 0.0488 1.0000
13.500 0.9704 0.09334 0.08560 0.0036 0.0476 1.0000
13.750 0.9653 0.09789 0.09012 0.0022 0.0461 1.0000
14.000 0.9482 0.10551 0.09793 -0.0018 0.0461 1.0000
14.250 0.9297 0.11378 0.10637 -0.0063 0.0461 1.0000
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Polar data table (+)
Polar graphs
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