12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il) Reynolds number: 500,000 Max Cl/Cd: 65.57 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-joukowsk-il-500000-n5.txt Download as CSV file: xf-joukowsk-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: 12% JOUKOWSKI AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.000 -1.2359 0.08740 0.08334 0.0069 1.0000 0.0169
-16.750 -1.2522 0.08056 0.07638 0.0029 1.0000 0.0171
-16.500 -1.2689 0.07391 0.06962 -0.0009 1.0000 0.0172
-16.250 -1.2850 0.06762 0.06320 -0.0045 1.0000 0.0173
-16.000 -1.2976 0.06202 0.05749 -0.0076 1.0000 0.0175
-15.750 -1.3097 0.05664 0.05198 -0.0105 1.0000 0.0176
-15.500 -1.3187 0.05188 0.04710 -0.0130 1.0000 0.0178
-15.250 -1.3258 0.04754 0.04264 -0.0152 1.0000 0.0180
-15.000 -1.3298 0.04379 0.03877 -0.0170 1.0000 0.0183
-14.750 -1.3332 0.04029 0.03515 -0.0184 1.0000 0.0185
-14.500 -1.3339 0.03730 0.03205 -0.0195 1.0000 0.0189
-14.250 -1.3338 0.03463 0.02926 -0.0201 1.0000 0.0191
-14.000 -1.3318 0.03237 0.02689 -0.0203 1.0000 0.0194
-13.750 -1.3304 0.03031 0.02473 -0.0200 1.0000 0.0197
-13.500 -1.3296 0.02847 0.02281 -0.0190 1.0000 0.0201
-13.250 -1.3270 0.02702 0.02129 -0.0175 1.0000 0.0205
-13.000 -1.3215 0.02591 0.02010 -0.0156 1.0000 0.0209
-12.750 -1.3101 0.02493 0.01905 -0.0141 1.0000 0.0214
-12.500 -1.2952 0.02404 0.01809 -0.0131 1.0000 0.0221
-12.250 -1.2782 0.02323 0.01720 -0.0122 1.0000 0.0228
-12.000 -1.2602 0.02245 0.01633 -0.0113 1.0000 0.0235
-11.750 -1.2422 0.02157 0.01542 -0.0105 1.0000 0.0244
-11.500 -1.2222 0.02084 0.01465 -0.0098 1.0000 0.0253
-11.250 -1.2010 0.02018 0.01393 -0.0092 1.0000 0.0263
-11.000 -1.1790 0.01957 0.01324 -0.0087 1.0000 0.0272
-10.750 -1.1572 0.01890 0.01253 -0.0081 1.0000 0.0283
-10.500 -1.1347 0.01827 0.01188 -0.0076 1.0000 0.0297
-10.250 -1.1113 0.01773 0.01130 -0.0072 1.0000 0.0312
-10.000 -1.0872 0.01724 0.01074 -0.0068 1.0000 0.0325
-9.750 -1.0636 0.01664 0.01014 -0.0064 1.0000 0.0342
-9.500 -1.0390 0.01614 0.00962 -0.0061 1.0000 0.0360
-9.250 -1.0138 0.01571 0.00914 -0.0058 1.0000 0.0380
-9.000 -0.9891 0.01520 0.00862 -0.0055 1.0000 0.0404
-8.750 -0.9636 0.01476 0.00818 -0.0052 1.0000 0.0430
-8.500 -0.9378 0.01435 0.00774 -0.0049 1.0000 0.0455
-8.250 -0.9122 0.01391 0.00731 -0.0047 1.0000 0.0489
-8.000 -0.8859 0.01356 0.00693 -0.0045 1.0000 0.0522
-7.750 -0.8598 0.01313 0.00653 -0.0043 1.0000 0.0565
-7.500 -0.8332 0.01280 0.00619 -0.0041 1.0000 0.0607
-7.250 -0.8069 0.01240 0.00583 -0.0039 1.0000 0.0664
-7.000 -0.7801 0.01207 0.00551 -0.0038 1.0000 0.0718
-6.750 -0.7533 0.01173 0.00520 -0.0036 1.0000 0.0786
-6.500 -0.7264 0.01139 0.00490 -0.0035 1.0000 0.0859
-6.250 -0.6993 0.01110 0.00462 -0.0034 1.0000 0.0935
-6.000 -0.6691 0.01079 0.00436 -0.0039 0.9818 0.1035
-5.750 -0.6344 0.01050 0.00411 -0.0053 0.9478 0.1153
-5.500 -0.6066 0.01028 0.00389 -0.0051 0.9166 0.1268
-5.250 -0.5819 0.01009 0.00368 -0.0043 0.8890 0.1384
-5.000 -0.5567 0.00991 0.00347 -0.0035 0.8642 0.1511
-4.750 -0.5309 0.00973 0.00327 -0.0029 0.8417 0.1648
-4.500 -0.5044 0.00956 0.00308 -0.0025 0.8203 0.1795
-4.250 -0.4776 0.00938 0.00290 -0.0021 0.7998 0.1954
-4.000 -0.4505 0.00922 0.00273 -0.0018 0.7801 0.2115
-3.750 -0.4231 0.00907 0.00257 -0.0016 0.7610 0.2283
-3.500 -0.3956 0.00893 0.00242 -0.0013 0.7424 0.2460
-3.000 -0.3399 0.00868 0.00217 -0.0010 0.7061 0.2814
-2.750 -0.3119 0.00857 0.00205 -0.0009 0.6882 0.2999
-2.500 -0.2838 0.00847 0.00196 -0.0008 0.6704 0.3177
-2.000 -0.2274 0.00829 0.00178 -0.0006 0.6353 0.3539
-1.750 -0.1991 0.00822 0.00171 -0.0005 0.6178 0.3718
-1.500 -0.1708 0.00816 0.00165 -0.0004 0.6006 0.3899
-1.250 -0.1424 0.00811 0.00160 -0.0003 0.5832 0.4080
-1.000 -0.1140 0.00806 0.00156 -0.0002 0.5661 0.4258
-0.750 -0.0855 0.00803 0.00153 -0.0002 0.5488 0.4437
-0.500 -0.0570 0.00801 0.00151 -0.0001 0.5313 0.4616
-0.250 -0.0285 0.00799 0.00149 -0.0001 0.5142 0.4790
0.000 0.0000 0.00799 0.00149 0.0000 0.4966 0.4965
0.250 0.0285 0.00799 0.00149 0.0001 0.4790 0.5141
0.500 0.0570 0.00801 0.00151 0.0001 0.4615 0.5313
0.750 0.0855 0.00803 0.00153 0.0002 0.4437 0.5488
1.000 0.1139 0.00806 0.00156 0.0003 0.4258 0.5660
1.250 0.1424 0.00811 0.00160 0.0003 0.4079 0.5832
1.500 0.1707 0.00816 0.00165 0.0004 0.3899 0.6006
1.750 0.1991 0.00822 0.00171 0.0005 0.3719 0.6179
2.000 0.2274 0.00829 0.00178 0.0006 0.3539 0.6353
2.500 0.2838 0.00847 0.00196 0.0008 0.3177 0.6704
2.750 0.3119 0.00857 0.00205 0.0009 0.2999 0.6881
3.000 0.3399 0.00868 0.00217 0.0010 0.2814 0.7061
3.250 0.3678 0.00880 0.00229 0.0012 0.2635 0.7241
3.500 0.3955 0.00893 0.00242 0.0013 0.2461 0.7424
3.750 0.4231 0.00907 0.00257 0.0016 0.2284 0.7610
4.000 0.4504 0.00922 0.00273 0.0018 0.2115 0.7800
4.250 0.4775 0.00938 0.00290 0.0021 0.1954 0.7998
4.500 0.5043 0.00956 0.00308 0.0025 0.1795 0.8203
4.750 0.5308 0.00973 0.00327 0.0029 0.1648 0.8417
5.000 0.5566 0.00991 0.00347 0.0035 0.1512 0.8642
5.250 0.5818 0.01009 0.00368 0.0043 0.1385 0.8890
5.500 0.6066 0.01028 0.00389 0.0051 0.1268 0.9167
5.750 0.6344 0.01050 0.00411 0.0053 0.1153 0.9479
6.000 0.6691 0.01079 0.00436 0.0039 0.1034 0.9821
6.250 0.6992 0.01110 0.00462 0.0034 0.0936 1.0000
6.500 0.7264 0.01140 0.00490 0.0035 0.0859 1.0000
6.750 0.7532 0.01173 0.00520 0.0036 0.0786 1.0000
7.000 0.7800 0.01207 0.00551 0.0038 0.0718 1.0000
7.250 0.8068 0.01240 0.00583 0.0039 0.0663 1.0000
7.500 0.8332 0.01280 0.00619 0.0041 0.0607 1.0000
7.750 0.8598 0.01313 0.00653 0.0043 0.0565 1.0000
8.000 0.8858 0.01356 0.00693 0.0045 0.0522 1.0000
8.250 0.9121 0.01391 0.00731 0.0047 0.0489 1.0000
8.500 0.9378 0.01435 0.00774 0.0050 0.0455 1.0000
8.750 0.9635 0.01476 0.00818 0.0052 0.0430 1.0000
9.000 0.9890 0.01519 0.00862 0.0055 0.0404 1.0000
9.250 1.0137 0.01571 0.00914 0.0058 0.0380 1.0000
9.500 1.0389 0.01614 0.00961 0.0061 0.0361 1.0000
9.750 1.0634 0.01664 0.01013 0.0064 0.0342 1.0000
10.000 1.0870 0.01724 0.01074 0.0068 0.0325 1.0000
10.250 1.1112 0.01773 0.01130 0.0072 0.0311 1.0000
10.500 1.1347 0.01827 0.01188 0.0077 0.0297 1.0000
10.750 1.1572 0.01890 0.01253 0.0081 0.0283 1.0000
11.000 1.1792 0.01956 0.01324 0.0087 0.0272 1.0000
11.250 1.2011 0.02018 0.01392 0.0092 0.0262 1.0000
11.500 1.2222 0.02084 0.01465 0.0098 0.0253 1.0000
11.750 1.2420 0.02158 0.01543 0.0105 0.0244 1.0000
12.000 1.2599 0.02245 0.01633 0.0114 0.0234 1.0000
12.250 1.2780 0.02322 0.01719 0.0122 0.0228 1.0000
12.500 1.2948 0.02404 0.01809 0.0132 0.0221 1.0000
12.750 1.3098 0.02492 0.01904 0.0142 0.0214 1.0000
13.000 1.3210 0.02590 0.02009 0.0156 0.0209 1.0000
13.250 1.3264 0.02702 0.02128 0.0176 0.0204 1.0000
13.500 1.3292 0.02844 0.02278 0.0191 0.0200 1.0000
13.750 1.3297 0.03031 0.02472 0.0201 0.0197 1.0000
14.000 1.3315 0.03233 0.02685 0.0204 0.0194 1.0000
14.250 1.3333 0.03461 0.02924 0.0202 0.0191 1.0000
14.500 1.3342 0.03720 0.03195 0.0196 0.0188 1.0000
14.750 1.3327 0.04026 0.03513 0.0185 0.0186 1.0000
15.000 1.3297 0.04371 0.03869 0.0171 0.0183 1.0000
15.250 1.3254 0.04751 0.04260 0.0153 0.0180 1.0000
15.500 1.3194 0.05169 0.04690 0.0132 0.0177 1.0000
15.750 1.3089 0.05664 0.05198 0.0106 0.0176 1.0000
16.000 1.2977 0.06187 0.05733 0.0078 0.0175 1.0000
16.250 1.2841 0.06761 0.06319 0.0046 0.0173 1.0000
16.500 1.2694 0.07367 0.06937 0.0011 0.0172 1.0000
16.750 1.2523 0.08035 0.07618 -0.0027 0.0170 1.0000
17.000 1.2360 0.08716 0.08310 -0.0067 0.0170 1.0000
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Polar data table (+)
Polar graphs
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