CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: CAP 21 (TraCFoil) (cap21c-il) Reynolds number: 100,000 Max Cl/Cd: 17.06 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-cap21c-il-100000.txt Download as CSV file: xf-cap21c-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: CAP 21 (TraCFoil)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5193 0.12777 0.12179 0.0309 1.0005 0.2046
-10.250 -0.5610 0.12513 0.11916 0.0243 1.0005 0.2124
-10.000 -0.5430 0.12042 0.11447 0.0248 1.0005 0.2138
-9.750 -0.5144 0.11730 0.11137 0.0267 1.0005 0.2160
-9.500 -0.4988 0.11466 0.10875 0.0271 1.0005 0.2205
-9.250 -0.5395 0.11051 0.10462 0.0207 1.0005 0.2286
-9.000 -0.4993 0.10777 0.10190 0.0241 1.0005 0.2313
-8.750 -0.4826 0.10531 0.09945 0.0247 1.0005 0.2365
-8.500 -0.5168 0.10085 0.09504 0.0192 1.0005 0.2443
-8.250 -0.4845 0.09824 0.09243 0.0216 1.0005 0.2467
-8.000 -0.4679 0.09582 0.09005 0.0222 1.0005 0.2517
-7.750 -0.4940 0.09142 0.08568 0.0177 1.0005 0.2603
-7.500 -0.4597 0.08964 0.08395 0.0205 1.0005 0.2645
-7.250 -0.4874 0.08554 0.07990 0.0161 1.0005 0.2755
-7.000 -0.5846 0.06395 0.05797 -0.0068 1.0005 0.2437
-6.750 -0.5684 0.06110 0.05514 -0.0062 1.0005 0.2446
-6.500 -0.5667 0.05560 0.04950 -0.0084 1.0005 0.2413
-6.250 -0.5760 0.04886 0.04242 -0.0113 1.0005 0.2419
-6.000 -0.5813 0.04305 0.03606 -0.0126 1.0005 0.2433
-5.750 -0.5538 0.04291 0.03630 -0.0108 1.0005 0.2463
-5.500 -0.5351 0.04157 0.03502 -0.0097 1.0005 0.2490
-5.250 -0.5207 0.03949 0.03284 -0.0091 1.0005 0.2525
-5.000 -0.5092 0.03666 0.02972 -0.0088 1.0005 0.2564
-4.750 -0.4953 0.03407 0.02679 -0.0085 1.0005 0.2595
-4.500 -0.4736 0.03303 0.02596 -0.0074 1.0005 0.2618
-4.250 -0.4527 0.03192 0.02494 -0.0064 1.0005 0.2645
-4.000 -0.3499 0.02977 0.02171 -0.0202 0.6655 0.2735
-3.750 -0.3310 0.02961 0.02052 -0.0184 0.5010 0.2758
-3.500 -0.3049 0.02915 0.01979 -0.0180 0.4648 0.2783
-3.250 -0.2784 0.02856 0.01897 -0.0178 0.4430 0.2811
-3.000 -0.2517 0.02798 0.01812 -0.0176 0.4274 0.2848
-2.750 -0.2246 0.02744 0.01719 -0.0176 0.4151 0.2889
-2.500 -0.1976 0.02687 0.01645 -0.0174 0.4048 0.2921
-2.250 -0.1698 0.02646 0.01601 -0.0171 0.3959 0.2951
-2.000 -0.1420 0.02617 0.01551 -0.0170 0.3884 0.2982
-1.750 -0.1136 0.02582 0.01506 -0.0169 0.3805 0.3023
-1.500 -0.0854 0.02559 0.01457 -0.0168 0.3737 0.3062
-1.250 -0.0574 0.02530 0.01436 -0.0166 0.3670 0.3099
-1.000 -0.0290 0.02514 0.01415 -0.0164 0.3614 0.3135
-0.750 -0.0004 0.02514 0.01397 -0.0163 0.3568 0.3172
-0.500 0.0286 0.02506 0.01385 -0.0162 0.3517 0.3210
-0.250 0.0565 0.02490 0.01377 -0.0160 0.3462 0.3248
0.000 0.0845 0.02504 0.01383 -0.0157 0.3415 0.3299
0.250 0.1131 0.02510 0.01395 -0.0156 0.3364 0.3356
0.500 0.1410 0.02512 0.01409 -0.0153 0.3321 0.3407
0.750 0.1690 0.02530 0.01428 -0.0150 0.3283 0.3464
1.000 0.1971 0.02563 0.01460 -0.0148 0.3245 0.3523
1.250 0.2242 0.02576 0.01501 -0.0145 0.3196 0.3583
1.500 0.2519 0.02603 0.01529 -0.0142 0.3151 0.3667
1.750 0.2788 0.02634 0.01568 -0.0138 0.3115 0.3755
2.000 0.3054 0.02685 0.01642 -0.0134 0.3082 0.3856
2.250 0.3316 0.02732 0.01716 -0.0130 0.3039 0.3974
2.500 0.3576 0.02766 0.01768 -0.0125 0.2996 0.4114
2.750 0.3838 0.02801 0.01808 -0.0119 0.2960 0.4316
3.000 0.4072 0.02865 0.01923 -0.0112 0.2920 0.4639
3.250 0.4275 0.02888 0.02035 -0.0100 0.2880 0.5726
3.500 0.4635 0.02870 0.02121 -0.0084 0.2831 0.9862
3.750 0.5043 0.02971 0.02197 -0.0109 0.2786 0.9995
4.000 0.5201 0.03119 0.02371 -0.0096 0.2741 0.9995
4.250 0.5385 0.03251 0.02510 -0.0085 0.2704 0.9995
4.500 0.5596 0.03351 0.02602 -0.0074 0.2672 0.9995
4.750 0.5849 0.03428 0.02651 -0.0066 0.2644 0.9995
5.000 0.5924 0.03707 0.02984 -0.0055 0.2593 0.9995
5.250 0.6090 0.03876 0.03164 -0.0047 0.2545 0.9995
5.500 0.6332 0.03939 0.03213 -0.0039 0.2511 0.9995
6.000 0.6488 0.04626 0.03950 -0.0035 0.2443 0.9995
6.250 0.6460 0.05133 0.04487 -0.0046 0.2406 0.9995
6.500 0.6708 0.05166 0.04510 -0.0035 0.2365 0.9995
6.750 0.7213 0.04852 0.04142 -0.0009 0.2335 0.9995
7.000 0.6645 0.06179 0.05553 -0.0065 0.2312 0.9995
7.250 0.6519 0.06931 0.06320 -0.0104 0.2343 0.9995
7.500 0.6646 0.07264 0.06651 -0.0104 0.2335 0.9995
8.000 0.5149 0.10125 0.09540 -0.0380 0.2576 0.9995
8.250 0.5280 0.10379 0.09791 -0.0379 0.2526 0.9995
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Polar data table (+)
Polar graphs
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