Joukovsky f=0% t=15% (joukowsk0015-jf) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: Joukovsky f=0% t=15% (joukowsk0015-jf) Reynolds number: 100,000 Max Cl/Cd: 34.99 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk0015-jf-100000.txt Download as CSV file: xf-joukowsk0015-jf-100000.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=15%
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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.9696 0.08180 0.07582 -0.0151 1.0000 0.1128
-13.500 -1.0359 0.06960 0.06337 -0.0226 1.0000 0.1117
-13.250 -1.0840 0.06183 0.05530 -0.0262 1.0000 0.1113
-13.000 -1.1207 0.05649 0.04966 -0.0272 1.0000 0.1116
-12.750 -1.1505 0.05261 0.04548 -0.0260 1.0000 0.1122
-12.500 -1.1756 0.04951 0.04200 -0.0235 1.0000 0.1131
-12.250 -1.1440 0.04814 0.04088 -0.0238 1.0000 0.1170
-12.000 -1.1381 0.04625 0.03889 -0.0227 1.0000 0.1202
-11.750 -1.1419 0.04375 0.03605 -0.0211 1.0000 0.1231
-11.500 -1.1383 0.04129 0.03332 -0.0197 1.0000 0.1263
-11.250 -1.1154 0.04018 0.03234 -0.0194 1.0000 0.1307
-11.000 -1.1056 0.03843 0.03036 -0.0182 1.0000 0.1353
-10.750 -1.0921 0.03652 0.02829 -0.0173 1.0000 0.1399
-10.500 -1.0708 0.03549 0.02734 -0.0168 1.0000 0.1454
-10.250 -1.0598 0.03390 0.02536 -0.0155 1.0000 0.1512
-10.000 -1.0345 0.03274 0.02444 -0.0153 1.0000 0.1573
-9.750 -1.0186 0.03149 0.02294 -0.0143 1.0000 0.1645
-9.500 -0.9951 0.03036 0.02197 -0.0139 1.0000 0.1714
-9.250 -0.9773 0.02928 0.02064 -0.0130 1.0000 0.1798
-9.000 -0.9530 0.02831 0.01987 -0.0127 1.0000 0.1877
-8.750 -0.9336 0.02725 0.01861 -0.0119 1.0000 0.1973
-8.500 -0.9095 0.02649 0.01802 -0.0114 1.0000 0.2066
-8.250 -0.8873 0.02558 0.01710 -0.0108 1.0000 0.2168
-8.000 -0.8662 0.02483 0.01618 -0.0101 1.0000 0.2284
-7.750 -0.8414 0.02414 0.01572 -0.0097 1.0000 0.2392
-7.500 -0.8183 0.02342 0.01502 -0.0091 1.0000 0.2510
-7.250 -0.7957 0.02274 0.01430 -0.0085 1.0000 0.2641
-7.000 -0.7721 0.02221 0.01382 -0.0079 1.0000 0.2772
-6.750 -0.7483 0.02168 0.01342 -0.0073 1.0000 0.2899
-6.500 -0.7255 0.02114 0.01295 -0.0066 1.0000 0.3033
-6.250 -0.7039 0.02065 0.01245 -0.0058 1.0000 0.3175
-6.000 -0.6841 0.02025 0.01208 -0.0047 1.0000 0.3316
-5.750 -0.6663 0.01990 0.01192 -0.0031 1.0000 0.3438
-5.500 -0.6524 0.01956 0.01163 -0.0012 1.0000 0.3563
-5.250 -0.6408 0.01929 0.01131 0.0009 1.0000 0.3697
-5.000 -0.6278 0.01912 0.01128 0.0028 1.0000 0.3814
-4.750 -0.6085 0.01896 0.01118 0.0035 0.9978 0.3951
-4.500 -0.5566 0.01887 0.01116 -0.0014 0.9839 0.4157
-4.250 -0.5048 0.01877 0.01113 -0.0061 0.9707 0.4361
-4.000 -0.4532 0.01866 0.01108 -0.0105 0.9579 0.4564
-3.750 -0.4052 0.01855 0.01104 -0.0140 0.9441 0.4755
-3.500 -0.3622 0.01847 0.01101 -0.0164 0.9289 0.4933
-3.250 -0.3245 0.01841 0.01101 -0.0177 0.9125 0.5100
-3.000 -0.2926 0.01836 0.01099 -0.0177 0.8951 0.5258
-2.750 -0.2651 0.01832 0.01094 -0.0170 0.8774 0.5415
-2.500 -0.2401 0.01830 0.01088 -0.0157 0.8598 0.5575
-2.250 -0.2157 0.01833 0.01100 -0.0140 0.8429 0.5705
-2.000 -0.1921 0.01831 0.01100 -0.0123 0.8266 0.5845
-1.750 -0.1688 0.01827 0.01092 -0.0106 0.8112 0.5997
-1.500 -0.1452 0.01825 0.01087 -0.0091 0.7946 0.6154
-1.250 -0.1212 0.01828 0.01097 -0.0074 0.7781 0.6282
-1.000 -0.0971 0.01827 0.01098 -0.0059 0.7622 0.6426
-0.750 -0.0730 0.01825 0.01093 -0.0045 0.7471 0.6581
-0.500 -0.0489 0.01823 0.01086 -0.0029 0.7334 0.6735
-0.250 -0.0246 0.01824 0.01093 -0.0013 0.7174 0.6868
0.000 0.0000 0.01825 0.01096 0.0000 0.7017 0.7017
0.250 0.0246 0.01824 0.01093 0.0013 0.6868 0.7174
0.500 0.0489 0.01823 0.01086 0.0029 0.6735 0.7334
0.750 0.0730 0.01825 0.01093 0.0045 0.6581 0.7470
1.000 0.0971 0.01827 0.01098 0.0059 0.6426 0.7622
1.250 0.1212 0.01828 0.01097 0.0074 0.6282 0.7781
1.500 0.1452 0.01825 0.01087 0.0091 0.6154 0.7946
1.750 0.1688 0.01827 0.01092 0.0106 0.5997 0.8112
2.000 0.1921 0.01831 0.01100 0.0123 0.5845 0.8266
2.250 0.2157 0.01833 0.01100 0.0140 0.5705 0.8429
2.500 0.2401 0.01830 0.01088 0.0157 0.5575 0.8598
2.750 0.2651 0.01832 0.01094 0.0170 0.5415 0.8774
3.000 0.2926 0.01836 0.01098 0.0177 0.5258 0.8951
3.250 0.3245 0.01840 0.01101 0.0177 0.5099 0.9125
3.500 0.3622 0.01847 0.01102 0.0164 0.4934 0.9289
3.750 0.4052 0.01855 0.01104 0.0140 0.4755 0.9441
4.000 0.4533 0.01866 0.01108 0.0105 0.4564 0.9579
4.250 0.5048 0.01877 0.01113 0.0060 0.4361 0.9707
4.500 0.5566 0.01887 0.01116 0.0014 0.4156 0.9839
4.750 0.6085 0.01896 0.01119 -0.0035 0.3951 0.9978
5.000 0.6278 0.01912 0.01128 -0.0028 0.3814 1.0000
5.250 0.6408 0.01929 0.01130 -0.0009 0.3697 1.0000
5.500 0.6524 0.01956 0.01163 0.0012 0.3562 1.0000
5.750 0.6664 0.01990 0.01192 0.0031 0.3438 1.0000
6.000 0.6842 0.02025 0.01208 0.0047 0.3316 1.0000
6.250 0.7039 0.02065 0.01245 0.0058 0.3175 1.0000
6.500 0.7255 0.02114 0.01295 0.0066 0.3033 1.0000
6.750 0.7483 0.02167 0.01342 0.0073 0.2899 1.0000
7.000 0.7721 0.02221 0.01382 0.0079 0.2772 1.0000
7.250 0.7957 0.02274 0.01429 0.0085 0.2641 1.0000
7.500 0.8182 0.02341 0.01502 0.0091 0.2510 1.0000
7.750 0.8414 0.02414 0.01571 0.0097 0.2392 1.0000
8.000 0.8662 0.02483 0.01618 0.0101 0.2284 1.0000
8.250 0.8873 0.02558 0.01709 0.0108 0.2167 1.0000
8.500 0.9095 0.02649 0.01802 0.0114 0.2066 1.0000
8.750 0.9337 0.02725 0.01860 0.0119 0.1973 1.0000
9.000 0.9530 0.02831 0.01987 0.0127 0.1877 1.0000
9.250 0.9774 0.02928 0.02064 0.0130 0.1798 1.0000
9.500 0.9951 0.03035 0.02196 0.0139 0.1714 1.0000
9.750 1.0186 0.03149 0.02294 0.0143 0.1645 1.0000
10.000 1.0345 0.03273 0.02444 0.0153 0.1573 1.0000
10.250 1.0598 0.03390 0.02536 0.0155 0.1512 1.0000
10.500 1.0708 0.03548 0.02733 0.0168 0.1454 1.0000
10.750 1.0923 0.03652 0.02829 0.0173 0.1399 1.0000
11.000 1.1058 0.03844 0.03037 0.0182 0.1353 1.0000
11.250 1.1156 0.04017 0.03234 0.0194 0.1307 1.0000
11.500 1.1388 0.04129 0.03331 0.0197 0.1263 1.0000
11.750 1.1421 0.04376 0.03607 0.0210 0.1231 1.0000
12.000 1.1384 0.04626 0.03889 0.0227 0.1202 1.0000
12.250 1.1445 0.04812 0.04086 0.0238 0.1170 1.0000
12.500 1.1758 0.04952 0.04200 0.0234 0.1131 1.0000
12.750 1.1508 0.05261 0.04548 0.0260 0.1122 1.0000
13.000 1.1205 0.05654 0.04971 0.0271 0.1115 1.0000
13.250 1.0843 0.06187 0.05535 0.0261 0.1113 1.0000
13.500 1.0357 0.06971 0.06348 0.0224 0.1117 1.0000
13.750 0.9679 0.08218 0.07620 0.0147 0.1128 1.0000
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