Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf) Reynolds number: 500,000 Max Cl/Cd: 58.22 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk0009-jf-500000.txt Download as CSV file: xf-joukowsk0009-jf-500000.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=9%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.9955 0.07812 0.07551 0.0078 1.0000 0.0151
-13.000 -1.0333 0.06592 0.06310 -0.0017 1.0000 0.0148
-12.750 -1.0612 0.05705 0.05400 -0.0087 1.0000 0.0147
-12.500 -1.0895 0.04945 0.04613 -0.0141 1.0000 0.0145
-12.250 -1.1028 0.04517 0.04167 -0.0162 1.0000 0.0146
-12.000 -1.1171 0.04158 0.03789 -0.0166 1.0000 0.0146
-11.750 -1.1277 0.03895 0.03506 -0.0149 1.0000 0.0148
-11.500 -1.1280 0.03641 0.03230 -0.0138 1.0000 0.0150
-11.250 -1.1217 0.03415 0.02981 -0.0128 1.0000 0.0153
-11.000 -1.1111 0.03219 0.02763 -0.0120 1.0000 0.0157
-10.750 -1.0968 0.03054 0.02576 -0.0112 1.0000 0.0162
-10.500 -1.0802 0.02907 0.02407 -0.0105 1.0000 0.0165
-10.250 -1.0672 0.02640 0.02111 -0.0097 1.0000 0.0169
-10.000 -1.0515 0.02416 0.01872 -0.0089 1.0000 0.0175
-9.750 -1.0310 0.02297 0.01746 -0.0084 1.0000 0.0181
-9.500 -1.0091 0.02198 0.01637 -0.0079 1.0000 0.0188
-9.250 -0.9867 0.02099 0.01527 -0.0074 1.0000 0.0196
-9.000 -0.9638 0.02003 0.01420 -0.0069 1.0000 0.0205
-8.750 -0.9397 0.01927 0.01332 -0.0065 1.0000 0.0213
-8.500 -0.9188 0.01772 0.01166 -0.0059 1.0000 0.0226
-8.250 -0.8945 0.01700 0.01092 -0.0056 1.0000 0.0240
-8.000 -0.8694 0.01637 0.01024 -0.0053 1.0000 0.0255
-7.750 -0.8439 0.01578 0.00956 -0.0050 1.0000 0.0269
-7.500 -0.8201 0.01476 0.00846 -0.0045 1.0000 0.0287
-7.250 -0.7949 0.01407 0.00776 -0.0043 1.0000 0.0311
-7.000 -0.7685 0.01364 0.00729 -0.0041 1.0000 0.0337
-6.750 -0.7428 0.01296 0.00655 -0.0038 1.0000 0.0367
-6.500 -0.7167 0.01241 0.00601 -0.0036 1.0000 0.0407
-6.250 -0.6899 0.01201 0.00556 -0.0034 1.0000 0.0448
-6.000 -0.6636 0.01143 0.00500 -0.0032 1.0000 0.0518
-5.750 -0.6369 0.01094 0.00453 -0.0030 1.0000 0.0598
-5.500 -0.6100 0.01051 0.00413 -0.0029 1.0000 0.0708
-5.250 -0.5832 0.01007 0.00376 -0.0028 1.0000 0.0863
-5.000 -0.5562 0.00967 0.00344 -0.0027 1.0000 0.1060
-4.750 -0.5293 0.00925 0.00315 -0.0026 1.0000 0.1322
-4.500 -0.5023 0.00886 0.00289 -0.0025 1.0000 0.1626
-4.250 -0.4753 0.00847 0.00265 -0.0025 1.0000 0.1965
-4.000 -0.4482 0.00813 0.00246 -0.0024 1.0000 0.2310
-3.750 -0.4211 0.00781 0.00228 -0.0023 1.0000 0.2664
-3.500 -0.3940 0.00751 0.00212 -0.0022 1.0000 0.3029
-3.250 -0.3669 0.00726 0.00200 -0.0021 1.0000 0.3380
-3.000 -0.3399 0.00701 0.00189 -0.0019 1.0000 0.3720
-2.750 -0.3133 0.00679 0.00181 -0.0017 1.0000 0.4059
-2.500 -0.2795 0.00660 0.00174 -0.0030 0.9882 0.4417
-2.250 -0.2411 0.00644 0.00170 -0.0052 0.9660 0.4771
-2.000 -0.2083 0.00632 0.00166 -0.0059 0.9383 0.5092
-1.750 -0.1825 0.00625 0.00162 -0.0051 0.9078 0.5378
-1.500 -0.1579 0.00621 0.00158 -0.0040 0.8789 0.5655
-1.250 -0.1327 0.00617 0.00155 -0.0030 0.8515 0.5926
-1.000 -0.1067 0.00613 0.00151 -0.0023 0.8247 0.6191
-0.750 -0.0803 0.00611 0.00148 -0.0016 0.7987 0.6453
-0.500 -0.0537 0.00610 0.00146 -0.0010 0.7732 0.6713
-0.250 -0.0269 0.00609 0.00145 -0.0005 0.7477 0.6970
0.000 0.0000 0.00608 0.00145 0.0000 0.7223 0.7222
0.250 0.0269 0.00609 0.00145 0.0005 0.6970 0.7478
0.500 0.0537 0.00610 0.00146 0.0010 0.6713 0.7733
0.750 0.0803 0.00611 0.00148 0.0016 0.6453 0.7987
1.000 0.1067 0.00613 0.00151 0.0023 0.6192 0.8247
1.250 0.1327 0.00617 0.00155 0.0030 0.5926 0.8515
1.500 0.1579 0.00621 0.00158 0.0040 0.5655 0.8789
1.750 0.1825 0.00625 0.00162 0.0051 0.5378 0.9078
2.000 0.2083 0.00632 0.00166 0.0059 0.5092 0.9383
2.250 0.2411 0.00644 0.00170 0.0052 0.4770 0.9660
2.500 0.2796 0.00660 0.00174 0.0030 0.4416 0.9881
2.750 0.3134 0.00679 0.00181 0.0017 0.4059 1.0000
3.000 0.3400 0.00701 0.00189 0.0019 0.3721 1.0000
3.250 0.3669 0.00726 0.00200 0.0021 0.3380 1.0000
3.500 0.3940 0.00751 0.00213 0.0022 0.3028 1.0000
3.750 0.4211 0.00781 0.00228 0.0023 0.2665 1.0000
4.000 0.4483 0.00813 0.00246 0.0024 0.2309 1.0000
4.250 0.4754 0.00847 0.00265 0.0024 0.1965 1.0000
4.500 0.5023 0.00886 0.00289 0.0025 0.1625 1.0000
4.750 0.5293 0.00925 0.00315 0.0026 0.1322 1.0000
5.000 0.5562 0.00967 0.00344 0.0027 0.1060 1.0000
5.250 0.5832 0.01007 0.00376 0.0028 0.0863 1.0000
5.500 0.6100 0.01051 0.00413 0.0029 0.0709 1.0000
5.750 0.6369 0.01094 0.00453 0.0031 0.0598 1.0000
6.000 0.6635 0.01143 0.00500 0.0032 0.0518 1.0000
6.250 0.6897 0.01202 0.00557 0.0034 0.0447 1.0000
6.500 0.7165 0.01241 0.00601 0.0036 0.0407 1.0000
6.750 0.7425 0.01296 0.00655 0.0039 0.0367 1.0000
7.000 0.7681 0.01364 0.00729 0.0042 0.0337 1.0000
7.250 0.7944 0.01407 0.00776 0.0044 0.0311 1.0000
7.500 0.8197 0.01474 0.00844 0.0046 0.0288 1.0000
7.750 0.8434 0.01576 0.00954 0.0051 0.0269 1.0000
8.000 0.8687 0.01636 0.01022 0.0054 0.0255 1.0000
8.250 0.8936 0.01698 0.01090 0.0058 0.0241 1.0000
8.500 0.9178 0.01770 0.01165 0.0061 0.0227 1.0000
8.750 0.9385 0.01927 0.01332 0.0067 0.0213 1.0000
9.000 0.9627 0.02002 0.01419 0.0071 0.0205 1.0000
9.250 0.9858 0.02097 0.01526 0.0076 0.0196 1.0000
9.500 1.0084 0.02198 0.01637 0.0080 0.0189 1.0000
9.750 1.0304 0.02298 0.01747 0.0085 0.0182 1.0000
10.000 1.0512 0.02415 0.01872 0.0089 0.0176 1.0000
10.250 1.0671 0.02641 0.02113 0.0097 0.0169 1.0000
10.500 1.0797 0.02918 0.02418 0.0105 0.0165 1.0000
10.750 1.0971 0.03045 0.02566 0.0112 0.0162 1.0000
11.000 1.1114 0.03210 0.02753 0.0120 0.0157 1.0000
11.250 1.1219 0.03409 0.02975 0.0128 0.0153 1.0000
11.500 1.1280 0.03638 0.03227 0.0138 0.0149 1.0000
11.750 1.1283 0.03885 0.03496 0.0149 0.0147 1.0000
12.000 1.1167 0.04165 0.03796 0.0166 0.0146 1.0000
12.250 1.1010 0.04541 0.04193 0.0161 0.0146 1.0000
12.500 1.0846 0.05018 0.04690 0.0136 0.0146 1.0000
12.750 1.0679 0.05596 0.05287 0.0095 0.0145 1.0000
13.000 1.0337 0.06596 0.06313 0.0016 0.0148 1.0000
13.250 0.9943 0.07856 0.07595 -0.0082 0.0151 1.0000
13.500 0.8425 0.12265 0.12039 -0.0360 0.0171 1.0000
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