12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il) Reynolds number: 500,000 Max Cl/Cd: 65.91 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-joukowsk-il-500000.txt Download as CSV file: xf-joukowsk-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -1.0771 0.14453 0.14175 0.0401 1.0000 0.0218
-18.250 -1.1215 0.12918 0.12614 0.0300 1.0000 0.0217
-18.000 -1.1460 0.11912 0.11591 0.0235 1.0000 0.0218
-17.750 -1.1659 0.11042 0.10705 0.0179 1.0000 0.0219
-17.500 -1.1818 0.10283 0.09931 0.0132 1.0000 0.0220
-17.250 -1.1968 0.09560 0.09194 0.0086 1.0000 0.0222
-17.000 -1.2095 0.08909 0.08529 0.0046 1.0000 0.0224
-16.750 -1.2210 0.08297 0.07903 0.0009 1.0000 0.0225
-16.500 -1.2321 0.07712 0.07303 -0.0026 1.0000 0.0227
-16.250 -1.2419 0.07169 0.06746 -0.0058 1.0000 0.0229
-16.000 -1.2502 0.06675 0.06238 -0.0086 1.0000 0.0231
-15.750 -1.2578 0.06201 0.05748 -0.0114 1.0000 0.0233
-15.500 -1.2660 0.05756 0.05293 -0.0133 1.0000 0.0236
-15.250 -1.2727 0.05347 0.04877 -0.0150 1.0000 0.0239
-15.000 -1.2757 0.04987 0.04511 -0.0166 1.0000 0.0243
-14.750 -1.2774 0.04652 0.04168 -0.0180 1.0000 0.0246
-14.500 -1.2774 0.04348 0.03857 -0.0193 1.0000 0.0251
-14.250 -1.2768 0.04063 0.03563 -0.0202 1.0000 0.0254
-14.000 -1.2752 0.03804 0.03293 -0.0209 1.0000 0.0259
-13.750 -1.2729 0.03567 0.03045 -0.0213 1.0000 0.0264
-13.500 -1.2694 0.03356 0.02823 -0.0213 1.0000 0.0269
-13.250 -1.2652 0.03170 0.02624 -0.0210 1.0000 0.0273
-13.000 -1.2618 0.02995 0.02437 -0.0202 1.0000 0.0278
-12.750 -1.2639 0.02799 0.02236 -0.0185 1.0000 0.0283
-12.500 -1.2608 0.02668 0.02101 -0.0164 1.0000 0.0289
-12.250 -1.2505 0.02568 0.01995 -0.0149 1.0000 0.0296
-12.000 -1.2359 0.02476 0.01897 -0.0138 1.0000 0.0306
-11.750 -1.2192 0.02392 0.01805 -0.0128 1.0000 0.0316
-11.500 -1.1998 0.02325 0.01726 -0.0120 1.0000 0.0325
-11.250 -1.1867 0.02185 0.01585 -0.0108 1.0000 0.0338
-11.000 -1.1671 0.02106 0.01502 -0.0101 1.0000 0.0351
-10.750 -1.1460 0.02036 0.01428 -0.0095 1.0000 0.0365
-10.500 -1.1235 0.01977 0.01360 -0.0089 1.0000 0.0378
-10.250 -1.1041 0.01876 0.01257 -0.0082 1.0000 0.0397
-10.000 -1.0813 0.01813 0.01192 -0.0077 1.0000 0.0417
-9.750 -1.0574 0.01760 0.01133 -0.0073 1.0000 0.0437
-9.500 -1.0349 0.01683 0.01053 -0.0068 1.0000 0.0460
-9.250 -1.0112 0.01622 0.00992 -0.0064 1.0000 0.0487
-9.000 -0.9860 0.01579 0.00944 -0.0060 1.0000 0.0514
-8.750 -0.9623 0.01508 0.00874 -0.0056 1.0000 0.0550
-8.500 -0.9369 0.01463 0.00827 -0.0053 1.0000 0.0586
-8.250 -0.9118 0.01408 0.00771 -0.0050 1.0000 0.0629
-8.000 -0.8861 0.01363 0.00727 -0.0048 1.0000 0.0679
-7.750 -0.8604 0.01313 0.00679 -0.0045 1.0000 0.0737
-7.500 -0.8341 0.01275 0.00641 -0.0043 1.0000 0.0799
-7.250 -0.8081 0.01226 0.00597 -0.0041 1.0000 0.0880
-7.000 -0.7817 0.01186 0.00559 -0.0039 1.0000 0.0966
-6.750 -0.7549 0.01150 0.00526 -0.0037 1.0000 0.1062
-6.500 -0.7282 0.01112 0.00493 -0.0036 1.0000 0.1176
-6.250 -0.7015 0.01074 0.00462 -0.0034 1.0000 0.1304
-6.000 -0.6745 0.01039 0.00434 -0.0033 1.0000 0.1445
-5.750 -0.6475 0.01007 0.00408 -0.0032 1.0000 0.1598
-5.500 -0.6204 0.00976 0.00385 -0.0031 1.0000 0.1761
-5.250 -0.5935 0.00945 0.00362 -0.0030 1.0000 0.1934
-5.000 -0.5666 0.00915 0.00342 -0.0028 1.0000 0.2117
-4.750 -0.5398 0.00888 0.00325 -0.0027 0.9995 0.2305
-4.500 -0.5004 0.00865 0.00309 -0.0051 0.9771 0.2532
-4.250 -0.4644 0.00843 0.00295 -0.0067 0.9534 0.2754
-3.750 -0.4119 0.00817 0.00272 -0.0053 0.8992 0.3147
-3.500 -0.3870 0.00807 0.00261 -0.0044 0.8757 0.3342
-3.250 -0.3610 0.00796 0.00249 -0.0037 0.8530 0.3534
-3.000 -0.3346 0.00786 0.00239 -0.0031 0.8316 0.3730
-2.750 -0.3078 0.00777 0.00229 -0.0026 0.8112 0.3930
-2.500 -0.2805 0.00769 0.00220 -0.0022 0.7913 0.4126
-2.250 -0.2529 0.00762 0.00212 -0.0019 0.7716 0.4321
-1.750 -0.1972 0.00750 0.00199 -0.0014 0.7329 0.4706
-1.500 -0.1693 0.00744 0.00193 -0.0011 0.7141 0.4897
-1.250 -0.1412 0.00740 0.00189 -0.0009 0.6953 0.5088
-1.000 -0.1131 0.00737 0.00185 -0.0007 0.6767 0.5277
-0.750 -0.0849 0.00735 0.00182 -0.0005 0.6582 0.5467
-0.500 -0.0566 0.00734 0.00180 -0.0003 0.6397 0.5656
-0.250 -0.0283 0.00733 0.00178 -0.0002 0.6214 0.5841
0.000 0.0000 0.00733 0.00178 0.0000 0.6028 0.6028
0.250 0.0283 0.00733 0.00178 0.0002 0.5842 0.6214
0.500 0.0566 0.00734 0.00180 0.0003 0.5655 0.6397
0.750 0.0848 0.00735 0.00182 0.0005 0.5467 0.6582
1.000 0.1130 0.00737 0.00185 0.0007 0.5278 0.6767
1.250 0.1412 0.00740 0.00188 0.0009 0.5088 0.6952
1.500 0.1692 0.00744 0.00193 0.0011 0.4897 0.7141
1.750 0.1972 0.00750 0.00199 0.0014 0.4706 0.7330
2.250 0.2528 0.00762 0.00212 0.0019 0.4321 0.7716
2.500 0.2805 0.00769 0.00220 0.0022 0.4126 0.7913
2.750 0.3077 0.00777 0.00229 0.0026 0.3930 0.8112
3.000 0.3346 0.00786 0.00239 0.0031 0.3730 0.8316
3.250 0.3610 0.00796 0.00249 0.0037 0.3534 0.8530
3.500 0.3870 0.00807 0.00261 0.0044 0.3342 0.8757
3.750 0.4118 0.00817 0.00272 0.0053 0.3148 0.8993
4.250 0.4643 0.00843 0.00295 0.0067 0.2754 0.9535
4.500 0.5004 0.00865 0.00309 0.0051 0.2532 0.9772
4.750 0.5398 0.00888 0.00325 0.0027 0.2305 0.9994
5.000 0.5666 0.00915 0.00342 0.0028 0.2118 1.0000
5.250 0.5935 0.00945 0.00362 0.0030 0.1935 1.0000
5.500 0.6204 0.00976 0.00385 0.0031 0.1761 1.0000
5.750 0.6475 0.01007 0.00408 0.0032 0.1598 1.0000
6.000 0.6745 0.01039 0.00434 0.0033 0.1445 1.0000
6.250 0.7014 0.01074 0.00462 0.0034 0.1304 1.0000
6.500 0.7282 0.01112 0.00493 0.0036 0.1175 1.0000
6.750 0.7549 0.01150 0.00526 0.0037 0.1062 1.0000
7.000 0.7816 0.01186 0.00559 0.0039 0.0966 1.0000
7.250 0.8081 0.01226 0.00597 0.0041 0.0879 1.0000
7.500 0.8340 0.01275 0.00641 0.0043 0.0799 1.0000
7.750 0.8604 0.01313 0.00678 0.0045 0.0737 1.0000
8.000 0.8860 0.01363 0.00727 0.0048 0.0679 1.0000
8.250 0.9118 0.01408 0.00770 0.0050 0.0629 1.0000
8.500 0.9368 0.01463 0.00827 0.0053 0.0586 1.0000
8.750 0.9622 0.01508 0.00874 0.0056 0.0550 1.0000
9.000 0.9858 0.01579 0.00943 0.0061 0.0514 1.0000
9.250 1.0111 0.01621 0.00992 0.0064 0.0486 1.0000
9.500 1.0349 0.01683 0.01052 0.0068 0.0460 1.0000
9.750 1.0573 0.01759 0.01133 0.0073 0.0437 1.0000
10.000 1.0812 0.01813 0.01192 0.0078 0.0417 1.0000
10.250 1.1039 0.01876 0.01256 0.0082 0.0397 1.0000
10.500 1.1231 0.01977 0.01360 0.0090 0.0379 1.0000
10.750 1.1457 0.02035 0.01427 0.0095 0.0365 1.0000
11.000 1.1669 0.02104 0.01501 0.0102 0.0350 1.0000
11.250 1.1864 0.02184 0.01584 0.0109 0.0338 1.0000
11.500 1.1994 0.02325 0.01726 0.0121 0.0325 1.0000
11.750 1.2187 0.02394 0.01807 0.0129 0.0316 1.0000
12.000 1.2359 0.02475 0.01896 0.0138 0.0305 1.0000
12.250 1.2507 0.02566 0.01994 0.0149 0.0296 1.0000
12.500 1.2610 0.02668 0.02101 0.0164 0.0289 1.0000
12.750 1.2641 0.02801 0.02238 0.0184 0.0283 1.0000
13.000 1.2610 0.03007 0.02449 0.0202 0.0277 1.0000
13.250 1.2658 0.03170 0.02623 0.0209 0.0273 1.0000
13.500 1.2704 0.03350 0.02816 0.0213 0.0268 1.0000
13.750 1.2734 0.03564 0.03043 0.0213 0.0264 1.0000
14.000 1.2758 0.03800 0.03289 0.0209 0.0259 1.0000
14.250 1.2771 0.04062 0.03561 0.0202 0.0254 1.0000
14.500 1.2779 0.04344 0.03852 0.0193 0.0250 1.0000
14.750 1.2775 0.04651 0.04167 0.0181 0.0247 1.0000
15.000 1.2763 0.04979 0.04502 0.0166 0.0243 1.0000
15.250 1.2725 0.05347 0.04876 0.0150 0.0239 1.0000
15.500 1.2659 0.05753 0.05289 0.0134 0.0235 1.0000
15.750 1.2580 0.06193 0.05741 0.0114 0.0233 1.0000
16.000 1.2506 0.06663 0.06226 0.0087 0.0231 1.0000
16.250 1.2419 0.07161 0.06738 0.0059 0.0229 1.0000
16.500 1.2324 0.07696 0.07288 0.0027 0.0227 1.0000
16.750 1.2211 0.08282 0.07888 -0.0008 0.0225 1.0000
17.000 1.2100 0.08886 0.08506 -0.0044 0.0224 1.0000
17.250 1.1972 0.09539 0.09172 -0.0084 0.0222 1.0000
17.500 1.1821 0.10260 0.09908 -0.0130 0.0220 1.0000
17.750 1.1656 0.11029 0.10691 -0.0178 0.0219 1.0000
18.000 1.1462 0.11889 0.11567 -0.0233 0.0218 1.0000
18.250 1.1218 0.12889 0.12585 -0.0297 0.0217 1.0000
18.500 1.0727 0.14533 0.14257 -0.0405 0.0219 1.0000
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