12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il) Reynolds number: 200,000 Max Cl/Cd: 48.73 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-joukowsk-il-200000-n5.txt Download as CSV file: xf-joukowsk-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -1.0043 0.12810 0.12391 0.0296 1.0000 0.0267
-16.500 -1.0489 0.11304 0.10859 0.0199 1.0000 0.0266
-16.250 -1.0759 0.10274 0.09807 0.0133 1.0000 0.0268
-16.000 -1.0963 0.09430 0.08944 0.0080 1.0000 0.0269
-15.750 -1.1143 0.08668 0.08162 0.0032 1.0000 0.0271
-15.500 -1.1290 0.08005 0.07479 -0.0009 1.0000 0.0274
-15.250 -1.1421 0.07402 0.06857 -0.0045 1.0000 0.0276
-15.000 -1.1491 0.06934 0.06382 -0.0070 1.0000 0.0279
-14.750 -1.1554 0.06485 0.05924 -0.0095 1.0000 0.0282
-14.500 -1.1609 0.06058 0.05487 -0.0118 1.0000 0.0285
-14.250 -1.1653 0.05658 0.05077 -0.0138 1.0000 0.0289
-14.000 -1.1688 0.05283 0.04691 -0.0157 1.0000 0.0293
-13.750 -1.1713 0.04934 0.04330 -0.0173 1.0000 0.0298
-13.500 -1.1725 0.04614 0.03998 -0.0186 1.0000 0.0304
-13.250 -1.1729 0.04320 0.03690 -0.0195 1.0000 0.0311
-13.000 -1.1719 0.04055 0.03407 -0.0201 1.0000 0.0319
-12.750 -1.1695 0.03820 0.03154 -0.0203 1.0000 0.0325
-12.500 -1.1679 0.03599 0.02930 -0.0202 1.0000 0.0331
-12.250 -1.1646 0.03414 0.02738 -0.0197 1.0000 0.0338
-12.000 -1.1599 0.03257 0.02573 -0.0187 1.0000 0.0346
-11.750 -1.1540 0.03119 0.02426 -0.0173 1.0000 0.0356
-11.500 -1.1446 0.02995 0.02290 -0.0159 1.0000 0.0367
-11.250 -1.1311 0.02880 0.02159 -0.0149 1.0000 0.0380
-11.000 -1.1181 0.02756 0.02033 -0.0139 1.0000 0.0393
-10.750 -1.1019 0.02654 0.01926 -0.0131 1.0000 0.0408
-10.500 -1.0842 0.02558 0.01821 -0.0123 1.0000 0.0426
-10.250 -1.0650 0.02468 0.01716 -0.0116 1.0000 0.0445
-10.000 -1.0468 0.02366 0.01615 -0.0109 1.0000 0.0464
-9.750 -1.0263 0.02285 0.01528 -0.0103 1.0000 0.0489
-9.500 -1.0046 0.02210 0.01443 -0.0097 1.0000 0.0516
-9.250 -0.9837 0.02124 0.01356 -0.0092 1.0000 0.0543
-9.000 -0.9612 0.02054 0.01281 -0.0087 1.0000 0.0576
-8.750 -0.9381 0.01986 0.01206 -0.0083 1.0000 0.0613
-8.500 -0.9152 0.01915 0.01136 -0.0078 1.0000 0.0653
-8.250 -0.8909 0.01859 0.01071 -0.0075 1.0000 0.0699
-8.000 -0.8673 0.01791 0.01007 -0.0071 1.0000 0.0752
-7.750 -0.8425 0.01738 0.00949 -0.0068 1.0000 0.0810
-7.500 -0.8180 0.01679 0.00892 -0.0065 1.0000 0.0879
-7.250 -0.7929 0.01626 0.00840 -0.0062 1.0000 0.0953
-7.000 -0.7674 0.01579 0.00792 -0.0059 1.0000 0.1042
-6.750 -0.7422 0.01528 0.00745 -0.0057 1.0000 0.1141
-6.500 -0.7165 0.01482 0.00702 -0.0054 1.0000 0.1248
-6.250 -0.6907 0.01438 0.00662 -0.0052 1.0000 0.1369
-6.000 -0.6647 0.01397 0.00624 -0.0050 1.0000 0.1501
-5.750 -0.6387 0.01357 0.00590 -0.0048 1.0000 0.1647
-5.500 -0.6125 0.01319 0.00558 -0.0046 1.0000 0.1802
-5.250 -0.5864 0.01283 0.00529 -0.0044 1.0000 0.1967
-5.000 -0.5603 0.01249 0.00502 -0.0042 1.0000 0.2141
-4.750 -0.5343 0.01217 0.00478 -0.0039 1.0000 0.2321
-4.500 -0.5021 0.01189 0.00456 -0.0049 0.9806 0.2526
-4.250 -0.4656 0.01163 0.00438 -0.0067 0.9536 0.2743
-4.000 -0.4318 0.01141 0.00421 -0.0078 0.9279 0.2958
-3.750 -0.4022 0.01124 0.00405 -0.0079 0.9022 0.3165
-3.500 -0.3751 0.01109 0.00392 -0.0075 0.8780 0.3362
-3.250 -0.3491 0.01095 0.00379 -0.0068 0.8548 0.3555
-3.000 -0.3234 0.01083 0.00366 -0.0060 0.8327 0.3749
-2.750 -0.2976 0.01072 0.00355 -0.0052 0.8117 0.3943
-2.500 -0.2715 0.01063 0.00344 -0.0045 0.7916 0.4136
-2.250 -0.2449 0.01054 0.00334 -0.0039 0.7716 0.4331
-2.000 -0.2182 0.01046 0.00325 -0.0034 0.7520 0.4521
-1.750 -0.1913 0.01039 0.00318 -0.0029 0.7327 0.4710
-1.500 -0.1643 0.01032 0.00311 -0.0024 0.7137 0.4900
-1.250 -0.1372 0.01027 0.00305 -0.0020 0.6948 0.5088
-1.000 -0.1099 0.01024 0.00300 -0.0015 0.6762 0.5276
-0.750 -0.0825 0.01021 0.00297 -0.0011 0.6576 0.5465
-0.500 -0.0551 0.01019 0.00294 -0.0007 0.6392 0.5651
-0.250 -0.0276 0.01018 0.00292 -0.0004 0.6208 0.5837
0.000 0.0000 0.01017 0.00291 0.0000 0.6024 0.6024
0.250 0.0276 0.01018 0.00292 0.0004 0.5837 0.6209
0.500 0.0550 0.01019 0.00294 0.0007 0.5651 0.6392
0.750 0.0825 0.01021 0.00297 0.0011 0.5464 0.6577
1.000 0.1098 0.01024 0.00300 0.0015 0.5277 0.6762
1.250 0.1371 0.01027 0.00305 0.0020 0.5088 0.6948
1.500 0.1643 0.01032 0.00311 0.0024 0.4900 0.7137
1.750 0.1913 0.01039 0.00318 0.0029 0.4710 0.7326
2.000 0.2182 0.01046 0.00325 0.0034 0.4521 0.7520
2.250 0.2449 0.01054 0.00334 0.0040 0.4331 0.7716
2.500 0.2715 0.01063 0.00344 0.0045 0.4136 0.7916
2.750 0.2976 0.01072 0.00355 0.0052 0.3943 0.8117
3.000 0.3234 0.01083 0.00366 0.0060 0.3749 0.8327
3.250 0.3491 0.01095 0.00379 0.0068 0.3554 0.8548
3.500 0.3751 0.01109 0.00392 0.0075 0.3363 0.8779
3.750 0.4021 0.01124 0.00405 0.0080 0.3165 0.9023
4.000 0.4318 0.01141 0.00421 0.0078 0.2958 0.9279
4.250 0.4656 0.01163 0.00438 0.0067 0.2743 0.9536
4.500 0.5021 0.01189 0.00456 0.0049 0.2526 0.9806
4.750 0.5343 0.01217 0.00478 0.0039 0.2321 1.0000
5.000 0.5603 0.01249 0.00502 0.0042 0.2142 1.0000
5.250 0.5864 0.01283 0.00529 0.0044 0.1966 1.0000
5.500 0.6125 0.01319 0.00558 0.0046 0.1802 1.0000
5.750 0.6386 0.01357 0.00590 0.0048 0.1646 1.0000
6.000 0.6647 0.01397 0.00625 0.0050 0.1501 1.0000
6.250 0.6907 0.01438 0.00662 0.0052 0.1369 1.0000
6.500 0.7165 0.01482 0.00702 0.0054 0.1248 1.0000
6.750 0.7421 0.01528 0.00745 0.0057 0.1141 1.0000
7.000 0.7674 0.01579 0.00792 0.0059 0.1042 1.0000
7.250 0.7929 0.01627 0.00840 0.0062 0.0953 1.0000
7.500 0.8180 0.01679 0.00892 0.0065 0.0879 1.0000
7.750 0.8424 0.01738 0.00949 0.0068 0.0810 1.0000
8.000 0.8672 0.01791 0.01007 0.0071 0.0752 1.0000
8.500 0.9151 0.01915 0.01136 0.0079 0.0653 1.0000
8.750 0.9381 0.01986 0.01206 0.0083 0.0613 1.0000
9.000 0.9611 0.02054 0.01281 0.0087 0.0577 1.0000
9.250 0.9836 0.02124 0.01355 0.0092 0.0543 1.0000
9.500 1.0044 0.02210 0.01442 0.0098 0.0516 1.0000
9.750 1.0261 0.02284 0.01527 0.0103 0.0488 1.0000
10.000 1.0467 0.02366 0.01615 0.0109 0.0464 1.0000
10.250 1.0649 0.02467 0.01715 0.0116 0.0445 1.0000
10.500 1.0840 0.02558 0.01820 0.0123 0.0426 1.0000
10.750 1.1018 0.02653 0.01925 0.0131 0.0408 1.0000
11.000 1.1179 0.02755 0.02032 0.0139 0.0393 1.0000
11.250 1.1308 0.02878 0.02157 0.0149 0.0380 1.0000
11.500 1.1442 0.02994 0.02289 0.0160 0.0367 1.0000
11.750 1.1536 0.03118 0.02424 0.0173 0.0355 1.0000
12.000 1.1596 0.03255 0.02571 0.0188 0.0346 1.0000
12.250 1.1643 0.03412 0.02736 0.0197 0.0338 1.0000
12.500 1.1676 0.03597 0.02927 0.0202 0.0331 1.0000
12.750 1.1693 0.03816 0.03151 0.0204 0.0325 1.0000
13.000 1.1716 0.04053 0.03406 0.0202 0.0318 1.0000
13.250 1.1728 0.04316 0.03686 0.0196 0.0311 1.0000
13.500 1.1726 0.04609 0.03992 0.0186 0.0304 1.0000
13.750 1.1714 0.04929 0.04326 0.0173 0.0298 1.0000
14.000 1.1691 0.05276 0.04684 0.0157 0.0293 1.0000
14.250 1.1657 0.05651 0.05069 0.0138 0.0289 1.0000
14.500 1.1615 0.06050 0.05478 0.0118 0.0285 1.0000
14.750 1.1559 0.06476 0.05914 0.0095 0.0282 1.0000
15.000 1.1498 0.06923 0.06370 0.0071 0.0279 1.0000
15.250 1.1416 0.07414 0.06871 0.0044 0.0275 1.0000
15.500 1.1292 0.08003 0.07478 0.0009 0.0273 1.0000
15.750 1.1145 0.08664 0.08158 -0.0032 0.0271 1.0000
16.000 1.0967 0.09419 0.08933 -0.0079 0.0269 1.0000
16.250 1.0759 0.10270 0.09803 -0.0133 0.0267 1.0000
16.500 1.0497 0.11276 0.10830 -0.0197 0.0266 1.0000
16.750 1.0040 0.12803 0.12384 -0.0295 0.0267 1.0000
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